AD 2006-07-10

[Federal Register Volume 71, Number 63 (Monday, April 3, 2006)]
[Rules and Regulations]
[Pages 16477-16481]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-3065]



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Federal Register / Vol. 71, No. 63 / Monday, April 3, 2006 / Rules 
and Regulations

[[Page 16477]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21593; Directorate Identifier 2002-NM-328-AD; 
Amendment 39-14537; AD 2006-07-10]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 727 airplanes. That AD 
currently requires repetitive visual inspections for cracking of the 
forward entry doorway forward frame and repair if necessary. That AD 
also provides an optional modification that constitutes terminating 
action. This new AD requires adding new post-repair and post-
modification inspections for previously repaired or modified airplanes, 
mandating the optional modification, and adding airplanes to the 
applicability of the AD. This AD results from reports of cracking of 
the forward entry doorway forward frame of airplanes previously 
modified. We are issuing this AD to prevent the loss of the structural 
integrity of the forward entry doorway due to cracking of the frame at 
Body Station 303.9, and consequent cracking of the fuselage skin and 
rapid decompression of the airplane.

DATES: This AD becomes effective May 8, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 8, 2006.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 91-09-07, amendment 39-
6982 (56 FR 18687, April 24, 1991). The existing AD applies to certain 
Boeing Model 727 series airplanes. That NPRM was published in the 
Federal Register on June 22, 2005 (70 FR 36064). That NPRM proposed to 
require adding new post-repair and post-modification inspections for 
previously repaired or modified airplanes, mandating the optional 
modification, and adding airplanes to the applicability of the AD.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Revise Paragraph (l) of the NPRM

    The Boeing Company requests that paragraph (l) of the NPRM be 
revised to apply the one-time inspections only to most Group 1 
airplanes. The commenter states that operators of most Group 1 
airplanes have been planning on doing the modification in accordance 
with AD 90-06-09, amendment 39-6488 (55 FR 8370, March 7, 1990) and 
Boeing Document D6-54860. The commenter asserts that mandating the 
modification in the final rule is redundant because it is already 
required by AD 90-06-09. The commenter further explains that Revision 7 
of Boeing Alert Service Bulletin (ASB) 727-53A0153, dated August 14, 
2003, added some new airplanes to the Group 1 list as well as all of 
the Group 2 airplanes.
    We do not agree. We do acknowledge that, for most Group 1 
airplanes, AD 90-06-09 also mandates the same modification as paragraph 
(l) of this AD, in that Boeing ASB 727-53-153 is referenced in Boeing 
Document D6-54860, ``Aging Airplane Service Bulletin Structural 
Modification Program--Model 727,'' Revision C, dated December 11, 1989, 
which is the appropriate source of service information required by AD 
90-06-09. We do not agree to require only the inspection for most of 
Group 1, since the service bulletin does not distinguish those 
airplanes that were added to Group 1. We have provided an alternative 
method of compliance statement in paragraph (n)(4) of this AD to allow 
credit for the modification accomplished in accordance with AD 90-06-
09.

Request To Revise the Compliance Time

    The Boeing Company also requests that paragraph (l) of the NPRM be 
revised to extend the grace period for some Group 1 airplanes and all 
of the Group 2 airplanes. The commenter suggests using the wording, 
``Before the accumulation of 60,000 total flight cycles, or within the 
earlier of 4 years or 7,200 flight cycles after the effective date of 
this AD.'' The commenter notes that some Group 1 airplanes and all of 
the Group 2 airplanes have been added to Revision 7 of Boeing ASB 727-
53A0153, and consequently, they were not addressed by Boeing Document 
D6-54860 or AD 90-06-09. The commenter explains that both Revision 7 of 
Boeing ASB 727-53A0153 and Boeing Document D6-54860 have a 60,000 
flight cycle threshold to do the modification. However, the commenter

[[Page 16478]]

states that the grace period in Boeing Document D6-54860 allows up to 4 
years beyond the 60,000 flight cycle threshold to allow operators to 
schedule the airplane modification during a major maintenance check 
period. The commenter advises that Model 727 airplanes fly an average 
of 1,800 flight cycles per year or 7,200 flight cycles in 4 years. For 
those airplanes past the 60,000 flight cycle threshold, safety would be 
mitigated by the inspections at 3,700 flight cycle intervals until 
reaching the 7,200 flight cycle or 4-year limit, whichever occurs 
first. The commenter states that revising the grace period also would 
provide the consistency with the compliance times specified in Boeing 
Document D6-54860.
    We agree that the compliance time may be revised for the reasons 
given by the commenter. We have revised paragraph (l) and added a new 
paragraph (m) of this AD to accommodate revision of the compliance 
time. This revision does not change the grace period for modification 
of Group 1 airplanes applicable to AD 90-06-09.

Editorial Changes

    We have revised paragraph (f) of this AD to correctly reference 
sub-paragraphs (f)(1) and (f)(2) of this AD.
    We also have revised this AD to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.
    In addition, we inadvertently specified in paragraph (k) of the 
NPRM that any cracking found during any HFEC inspection required 
certain corrective actions. Our intention was to specify that any 
cracking found during any inspection would require certain corrective 
actions. We have revised paragraph (k) of this AD to state that, if any 
cracking is detected during any inspection, certain corrective actions 
must be accomplished.

Explanation of Change To Applicability

    We have revised the applicability of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 1,038 Model 727 airplanes of the affected design in 
the worldwide fleet. This AD will affect about 616 airplanes of U.S. 
registry.
    The actions that are required by AD 91-09-07 and retained in this 
AD take about 58 work hours per airplane, at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of the 
currently required actions is $3,770 per airplane, per inspection 
cycle.
    The new inspections will take about 5 to 6 work hours per airplane, 
depending on the airplane configuration, at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of the 
new actions required by this AD is between $325 and $390 per airplane, 
per inspection cycle.
    The terminating action specified in this AD will affect airplanes 
on which the previous optional modification has not been accomplished, 
and will take between 14 and 40 work hours per airplane, depending on 
the airplane configuration, at an average labor rate of $65 per work 
hour. Required parts for the terminating modification will cost between 
$877 and $6,749 per airplane, depending on the airplane configuration. 
Based on these figures, the estimated cost of the terminating action 
specified in this AD is between $1,787 and $9,349 per airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-6982 (56 FR 18687, April 24, 1991) and by adding 
the following new airworthiness directive (AD):

2006-07-10 Boeing: Amendment 39-14537. Docket No. FAA-2005-21593; 
Directorate Identifier 2002-NM-328-AD.

Effective Date

    (a) This AD becomes effective May 8, 2006.

Affected ADs

    (b) This AD supersedes AD 91-09-07.

Applicability

    (c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F airplanes, certificated in any category; 
as identified in Boeing Alert Service Bulletin 727-53A0153, Revision 
7, dated August 14, 2003.

Unsafe Condition

    (d) This AD was prompted by reports of cracking of the forward 
frame of the forward

[[Page 16479]]

entry doorway of airplanes previously modified. We are issuing this 
AD to prevent the loss of the structural integrity of the forward 
entry doorway due to cracking at Body Station (BS) 303.9, and 
consequent cracking of the fuselage skin and rapid decompression of 
the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 91-09-07

    (f) For airplanes listed in Boeing Service Bulletin 727-53-0153, 
Revision 5, dated December 14, 1989: Visually inspect the forward 
entry doorway frame for cracks in accordance with Boeing Service 
Bulletin 727-53-0153, dated February 1, 1980, or Revisions 1 through 
5, at the earlier of the times indicated in subparagraphs (f)(1) or 
(f)(2) of this AD. Repeat the inspection at intervals not to exceed 
3,700 landings until accomplishment of the one-time high frequency 
eddy current (HFEC) inspection for cracking and the one-time 
dimensional inspection for anomalies required by paragraph (i) of 
this AD, or the one-time dimensional inspection for anomalies and 
the initial HFEC inspection for cracking of the forward frame of the 
forward entry doorway at BS 303.9 specified in paragraph (h) of this 
AD, as applicable.
    (1) Within the next 1,850 landings after March 11, 1983 (the 
effective date of AD 83-03-01, amendment 39-4561), or prior to 
accumulating a total of 25,000 landings, whichever occurs later; or
    (2) Within the next 1,850 landings after May 16, 1986 (the 
effective date of AD 83-03-01 R1, amendment 39-5283), or prior to 
accumulating a total of 15,000 landings, whichever occurs later.
    (g) For airplanes modified in accordance with Boeing Service 
Bulletin 727-53-0153, dated February 1, 1980; through Revision 4, 
dated November 8, 1985; conduct the inspections described in 
paragraph (f) of this AD prior to the accumulation of 10,000 
landings after the modification or within the next 3,700 landings 
after May 28, 1991 (the effective date of AD 91-09-07), whichever 
occurs later. Repeat the inspection at intervals not to exceed 3,700 
landings until accomplishment of the one-time HFEC inspection for 
cracking and the one-time dimensional inspection for anomalies 
required by paragraph (i) of this AD, or the one-time dimensional 
inspection for anomalies and the initial HFEC inspection for 
cracking of the forward frame of the forward entry doorway at BS 
303.9 specified in paragraph (h) of this AD, as applicable.

New Requirements of This AD

Repetitive Inspections for Certain Airplanes

    (h) For Group 1 airplanes as defined by Boeing Alert Service 
Bulletin (ASB) 727-53A0153, Revision 7, dated August 14, 2003, with 
the exception of certain Group 1 airplanes specified in paragraph 
(i) of this AD: Perform a one-time dimensional inspection for 
anomalies (e.g., minimum dimension requirements, jagged edges, 
chafing, nicks, or gouges) of the web cutouts at stringers S-15 and 
S-16, and HFEC inspections for cracking of the forward frame of the 
forward entry doorway at BS 303.9; in accordance with Figure 1 of 
the Accomplishment Instructions of Revision 7 of the ASB at the 
times specified in paragraph (h)(1) or (h)(2) of this AD, as 
applicable. With the exception of the one-time dimensional 
inspection (Step 1 of Figure 1) of the web cutouts at S-15L and S-
16L, repeat the HFEC inspections for cracking of the forward frame 
of the forward entry doorway at BS 303.9 at intervals not to exceed 
3,700 flight cycles until the requirements of paragraph (l) of this 
AD have been accomplished.
    (1) For Group 1 airplanes that have not been modified or 
repaired in accordance with any issue of the service bulletin 
through Revision 7 inclusive specified in Table 1 of this AD: 
Perform the inspection before the accumulation of 15,000 total 
flight cycles, or within 1,800 flight cycles after the effective 
date of this AD, whichever occurs later.

                                      Table 1.--Service bulletin Revisions
----------------------------------------------------------------------------------------------------------------
            Service bulletin                      Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 727-53-153......  Original.....................  February 1, 1980.
Boeing Service Bulletin 727-53-153......  Revision 1...................  June 19, 1981.
Boeing Service Bulletin 727-53-153......  Revision 2...................  December 3, 1982.
Boeing Service Bulletin 727-53-153......  Revision 3...................  June 17, 1983.
Boeing Service Bulletin 727-53-153......  Revision 4...................  November 8, 1985.
Boeing Service Bulletin 727-53-0153.....  Revision 5...................  December 14, 1989.
Boeing Service Bulletin 727-53-0153.....  Revision 6...................  August 27, 1992.
Boeing Alert Service Bulletin 727-53A153  Revision 7...................  August 14, 2003.
----------------------------------------------------------------------------------------------------------------

    (2) For Group 1 airplanes that have been modified as specified 
in Boeing Repair Kit 65C20303-1 in accordance with any issue of the 
service bulletin through Revision 4 inclusive as specified in Table 
1 of this AD: Perform the inspection before the accumulation of 
10,000 flight cycles after the modification, or within 1,800 flight 
cycles after the effective date of this AD, whichever occurs later.

One-Time Inspections and Terminating Actions for Certain Other 
Airplanes

    (i) For Group 1 airplanes, as defined by Boeing ASB 727-53A0153, 
Revision 7, dated August 14, 2003, that have been modified in 
accordance with Revision 5 or 6 of Boeing Service Bulletin 727-53-
0153 as specified in Table 1 of this AD, or that have been repaired 
in accordance with Boeing Repair Kit 65C20303-8 or -25 as specified 
in Revision 2 through Revision 6 inclusive of the service bulletin 
as specified in Table 1 of this AD: Within 4,500 flight cycles after 
the effective date of this AD, do a one-time HFEC for cracking and a 
dimensional inspection for any anomaly (e.g., minimum dimension 
requirements, jagged edges, chafing, nicks or gouges) of the web 
cutouts at stringers S-15L and S-16L of the forward frame of the 
forward entry doorway at BS 303.9, in accordance with Step 1 and 
Step 2 of Figure 1 of the Accomplishment Instructions of Boeing ASB 
727-53A0153, Revision 7, dated August 14, 2003. For these airplanes, 
accomplishment of the HFEC, dimensional inspections, and any 
applicable corrective actions, constitutes terminating action for 
all the repetitive inspection requirements of this AD.

Inspections for Group 2 Airplanes

    (j) For Group 2 airplanes, as defined by Boeing ASB 727-53A0153, 
Revision 7, dated August 14, 2003, that have not been modified or 
repaired in accordance with Revision 7 of the ASB: Before the 
accumulation of 17,000 total flight cycles, or within 4,500 flight 
cycles after the effective date of this AD, whichever occurs later, 
perform a one-time dimensional inspection for anomalies (e.g., 
minimum dimension requirements, jagged edges, chafing, nicks, or 
gouges) of the web cutouts at stringers S-15 and S-16, and HFEC 
inspections for cracking of the forward frame of the forward entry 
doorway at BS 303.9; in accordance with Figure 2 of the 
Accomplishment Instructions of Revision 7 of the ASB. With the 
exception of the one-time dimensional inspection (Step 1 of Figure 
2) of the web cutouts at S-15L and S-16L, repeat the HFEC 
inspections for cracking of the forward frame of the forward entry 
doorway at BS 303.9 at intervals not to exceed 3,700 flight cycles 
until the requirements of paragraph (l) of this AD have been 
accomplished.

Corrective Actions

    (k) If any cracking is detected during any inspection, or any 
anomaly is detected during any dimensional inspection required by 
this AD: Before further flight, accomplish the actions in paragraph 
(k)(1) or (k)(2) of this AD, as applicable.

[[Page 16480]]

    (1) For any cracking that is within the limits specified in the 
Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7, 
dated August 14, 2003: Repair the cracking in accordance with 
Revision 7 of the ASB.
    (2) For any cracking that is outside the limits specified in the 
Accomplishment Instructions of Boeing ASB 727-53A0153, Revision 7, 
dated August 14, 2003, or for any anomaly that is detected during 
any dimensional inspection required by this AD: Repair in accordance 
with a method approved by the Manager, Seattle Aircraft 
Certification (ACO), FAA; or in accordance with the procedures 
specified in paragraph (n) of this AD.

Terminating Actions for Certain Airplanes

    (l) For airplanes specified in paragraph (l)(1) or (l)(2) of 
this AD: At the time specified in paragraph (m) of this AD, perform 
the inspections specified in Figure 1 or Figure 2, as applicable, of 
Revision 7 of Boeing ASB 727-53A0153, dated August 14, 2003, and as 
specified by paragraph (h) or (j) of this AD, as applicable. Before 
further flight, following the inspections, modify the forward frame 
in accordance with the Accomplishment Instructions of Revision 7 of 
the ASB. Concurrent accomplishment of the inspections and 
modification constitutes terminating action for the repetitive 
inspections required by this AD.
    (1) Group 1 airplanes that have not been modified or repaired in 
accordance with Boeing Repair Kit 65C20303-8 or -25, as specified in 
Boeing Service Bulletin 727-53-153, Revision 2, dated December 3, 
1982; Revision 3, dated June 17, 1983; or Revision 4, dated November 
8, 1985; Boeing Service Bulletin 727-53-0153, Revision 5, dated 
December 14, 1989; or Revision 6, dated August 27, 1992; or Boeing 
ASB 727-53A0153, Revision 7, dated August 14, 2003.
    (2) Group 2 airplanes that have not been repaired or modified in 
accordance with Revision 7 of Boeing ASB 727-53A0153, dated August 
14, 2003.

    Note 1: Accomplishment of the terminating actions specified in 
paragraph (i) or (l) of this AD does not relieve the operator of 
responsibility to comply with the inspection requirements of the 
operator's standard structural maintenance program.

Compliance Times for the Requirements of Paragraph (l) of This AD

    (m) Accomplish the actions required in paragraph (l) of this AD 
at the later of the times specified in paragraph (m)(1) or (m)(2) of 
this AD.
    (1) Prior to the accumulation of 60,000 total flight cycles.
    (2) Within 48 months or 7,200 flight cycles after the effective 
date of this AD, whichever occurs first.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.
    (4) AMOCs approved previously in accordance with AD 91-09-07, 
amendment 39-6982, are approved as AMOCs with the corresponding 
requirements and provisions of this AD.
    (5) Accomplishment of the actions specified in paragraph (l) of 
this AD constitutes an AMOC with paragraph A. of AD 90-06-09, 
amendment 39-6488, only for the structural modification requirements 
of Boeing Service Bulletin 727-53-153, as specified in Boeing 
Document D6-54860, Revision C, dated December 11, 1989, which is the 
appropriate source of service information specified by AD 90-06-09.

Material Incorporated by Reference

    (o) You must use the applicable service bulletins or alert 
service bulletin specified in Table 2 of this AD to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. Boeing Service Bulletin 727-53-153, Revision 1, including 
Addendum, dated June 19, 1981, contains the following effective 
pages:

------------------------------------------------------------------------
                                   Revision level
            Page No.               shown on page     Date shown on page
------------------------------------------------------------------------
1-25............................  1..............  June 19, 1981.
26..............................  Original.......  February 1, 1980.
------------------------------------------------------------------------
                                Addendum
------------------------------------------------------------------------
1-6.............................  1..............  June 19, 1981.
------------------------------------------------------------------------

    Boeing Service Bulletin 727-53-153, Revision 4, including 
Addendum, dated November 8, 1985, contains the following effective 
pages:

------------------------------------------------------------------------
                                      Revision
            Page number             level shown     Date shown on page
                                      on page
------------------------------------------------------------------------
1-11, 13-19, 21...................            4  November 8, 1985.
12, 20, 22........................            3  June 17, 1983.
------------------------------------------------------------------------
                                Addendum
------------------------------------------------------------------------
1, 4..............................            3  June 17, 1983.
------------------------------------------------------------------------
2, 3, 5, 6........................            4  November 8, 1985.
------------------------------------------------------------------------

    The Director of the Federal Register approved the incorporation 
by reference of these documents in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 
3707, Seattle, Washington 98124-2207, for a copy of this service 
information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
room PL-401, Nassif Building, Washington, DC; on the Internet at 
<a href="http://dms.dot.gov">http://dms.dot.gov</a>; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

                                  Table 2.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
             Service bulletin                     Revision level                          Date
----------------------------------------------------------------------------------------------------------------
1. Boeing Service Bulletin 727-53-153....  Original...................  February 1, 1980.
2. Boeing Service Bulletin 727-53-153,     Revision 1.................  June 19, 1981.
 including Addendum.
3. Boeing Service Bulletin 727-53-153,     Revision 2.................  December 3, 1982.
 including Addendum.
4. Boeing Service Bulletin 727-53-153,     Revision 3.................  June 17, 1983.
 including Addendum.
5. Boeing Service Bulletin 727-53-153,     Revision 4.................  November 8, 1985.
 including Addendum.
6. Boeing Service Bulletin 727-53-0153,    Revision 5.................  December 14, 1989.
 including Addendum.
7. Boeing Alert Service Bulletin 727-      Revision 7.................  August 14, 2003.
 53A0153.
----------------------------------------------------------------------------------------------------------------



[[Page 16481]]

    Issued in Renton, Washington, on March 17, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3065 Filed 3-31-06; 8:45 am]
BILLING CODE 4910-13-P