AD 2001-02-09

[Federal Register Volume 66, Number 19 (Monday, January 29, 2001)]
[Rules and Regulations]
[Pages 8077-8079]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-2111]



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Federal Register / Vol. 66, No. 19 / Monday, January 29, 2001 / Rules 
and Regulations

[[Page 8077]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-184-AD; Amendment 39-12093; AD 2001-02-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 757-200 series airplanes, that 
currently requires inspections to detect cracking on the free edge of 
the tang, if necessary, and of the fastener holes in the lower spar 
chord; and various follow-on actions. That AD also provides for an 
optional terminating action for the repetitive inspections. This 
amendment adds inspections to detect additional cracking of the 
fastener holes in the lower spar chord. This amendment also adds an 
optional terminating modification. This amendment is prompted by the 
issuance of new service information. The actions specified by this AD 
are intended to detect and correct fatigue cracking in the lower spar 
chord, which could result in reduced structural integrity of the engine 
strut.

DATES: Effective March 5, 2001.
    The incorporation by reference of Boeing Service Bulletin 757-54-
0031, Revision 4, dated November 11, 1999, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
March 5, 2001.
    The incorporation by reference of Boeing Service Bulletin 757-54-
0031, Revision 2, dated December 19, 1996, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of March 28, 1997 (62 FR 11760, March 13, 1997).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2776; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-06-04, 
amendment 39-9961 (62 FR 11760, March 13, 1997), which is applicable to 
certain Boeing Model 757-200 series airplanes, was published in the 
Federal Register on October 10, 2000 (65 FR 60129). The action proposed 
to continue to require inspections to detect cracking on the free edge 
of the tang, if necessary, and of the fastener holes in the lower spar 
chord; and various follow-on actions. The action also proposed to 
continue to provide for an optional terminating action for the 
repetitive inspections. The action also proposed to require additional 
inspections to detect additional cracking of the fastener holes in the 
lower spar chord; and to add an optional terminating modification.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 418 Model 757-200 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 151 
airplanes of U.S. registry will be affected by this AD.
    The inspections that are currently required by AD 97-06-04 take 
approximately 52 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $471,120, or $3,120 per airplane.
    The new inspections that are required in this AD action will take 
approximately 4 work hours per inspection, per airplane to accomplish, 
at an average labor rate of $60 per work hour. Based on these figures, 
the cost impact of the new requirements of this AD on U.S. operators is 
estimated to be $36,240, or $240 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules

[[Page 8078]]

Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. Section 39.13 is amended by removing amendment 39-9961 (62 FR 
11760, March 13, 1997), and by adding a new airworthiness directive 
(AD), amendment 39-12093, to read as follows:

2001-02-09  Boeing: Amendment 39-12093. Docket 2000-NM-184-AD. 
Supersedes AD 97-06-04, Amendment 39-9961.

    Applicability: Model 757-200 series airplanes having line 
numbers 1 through 736 inclusive, powered by Rolls Royce engines, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (n) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking of the lower spar chord, 
which could result in reduced structural integrity of the engine 
strut, accomplish the following:

Restatement of Requirements of AD 97-06-04

Repetitive Inspections

    (a) Prior to the accumulation of 15,000 total flight cycles, or 
within 60 days after March 28, 1997 (the effective date of AD 97-06-
04, amendment 39-9961), whichever occurs later: Perform an eddy 
current inspection to detect cracking on the free edge of the tang, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 757-54-0031, Revision 2, dated December 19, 1996, or 
Revision 4, dated November 11, 1999. Repeat this inspection 
thereafter at intervals not to exceed 3,000 flight cycles until the 
inspection required by paragraph (d) of this AD is accomplished.

    Note 2: The inspection required by paragraph (a) of this AD need 
not be performed on airplanes on which the inspection required by 
paragraph (d) of this AD is performed prior to the compliance time 
specified in paragraph (a) of this AD.

Follow-On Actions

    (b) If any cracking is found during the inspection required by 
paragraph (a) of this AD, and the cracking is within the limits 
specified in Boeing Service Bulletin 757-54-0031, Revision 2, dated 
December 19, 1996, or Revision 4, dated November 11, 1999: Prior to 
further flight, remove the midchord channels, stop-drill the 
cracking, and install a repair in accordance with the service 
bulletin. No further action is required by paragraph (a) of this AD.
    (c) If any cracking is found, and the cracking is outside the 
limits specified in Boeing Service Bulletin 757-54-0031, Revision 2, 
dated December 19, 1996, or Revision 4, dated November 11, 1999: 
Prior to further flight, replace the lower spar chord with a new or 
serviceable chord in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA.

Bolt Hole Inspection

    (d) Perform an eddy current inspection (bolt hole inspection) to 
detect cracking of the two fastener holes in the lower spar chord, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 757-54-0031, Revision 2, dated December 19, 1996, or 
Revision 4, dated November 11, 1999, at the time specified in 
paragraph (d)(1) or (d)(2) of this AD, as applicable. Accomplishment 
of this inspection terminates the inspections required by paragraph 
(a) of this AD.
    (1) For airplanes on which the stiffening straps have been 
removed from the midchord in accordance with Boeing Service Bulletin 
757-54-0028 prior to the effective date of this AD: Accomplish the 
inspection at the time specified in Paragraph 1.D. (``Description'') 
of Boeing Service Bulletin 757-54-0031, Revision 2, dated December 
19, 1996, or Revision 4, dated November 11, 1999.
    (2) For airplanes other than those identified in paragraph 
(d)(1) of this AD: Accomplish the inspection prior to the 
accumulation of 18,000 total flight cycles, or within 60 days after 
March 28, 1997, whichever occurs later.
    (e) Accomplish either paragraph (e)(1) or (e)(2) of this AD, as 
applicable, in accordance with Boeing Service Bulletin 757-54-0031, 
Revision 2, dated December 19, 1996, or Revision 4, dated November 
11, 1999.
    (1) If any fastener installed as a result of an inspection 
required by paragraph (d) of this AD has a diameter of \5/8\-inch or 
greater: Install the repair prior to the accumulation of the number 
of flight cycles specified in the ``Subsequent Inspection Interval'' 
column of the Threshold Table included in Paragraph 1.E. 
(``Compliance'') of Boeing Service Bulletin 757-54-0031, Revision 2, 
dated December 19, 1996, or Revision 4, dated November 11, 1999.
    (2) If any fastener installed as a result of an inspection 
required by paragraph (d) of this AD has a diameter of less than \5/
8\-inch: Repeat the bolt hole inspection required by paragraph (d) 
of this AD prior to the accumulation of the number of flight cycles 
specified in the ``Subsequent Inspection Interval'' column of the 
Threshold Table included in Paragraph 1.E. (``Compliance'') of the 
service bulletin until the repair specified in paragraph (h) of this 
AD is installed.

Optional Terminating Action

    (f) Installation of the repair in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 757-54-0031, 
Revision 2, dated December 19, 1996, or Revision 4, dated November 
11, 1999, constitutes terminating action for the requirements in 
paragraphs (a) and (d) of this AD.

New Requirements of This AD

Revised Service Information

    (g) Except as provided by paragraphs (c) and (l)(3) of this AD: 
As of the effective date of this new AD, Boeing Service Bulletin 
757-54-0031, Revision 4, dated November 11, 1999, must be used for 
accomplishment of the actions required by this AD.

Second Bolt Hole Inspection

    (h) Within 6,000 flight cycles after accomplishment of paragraph 
(d) of this AD, or within 60 days after the effective date of this 
AD, whichever occurs later: Perform a second eddy current inspection 
(bolt hole inspection) to detect cracking of the two fastener holes 
in the lower spar chord, in accordance with Part IV of the 
Accomplishment Instructions of Boeing Service Bulletin 757-54-0031, 
Revision 4, dated November 11, 1999. If no cracking is found during 
the inspection required by this paragraph, no further action is 
required by this paragraph.

Third Bolt Hole Inspection

    (i) After accomplishment of the inspection required by paragraph 
(h) of this AD, when the airplane has reached the flight cycle 
threshold as defined by the flight cycle threshold formula on page 
9, Paragraph 1.E. (``Compliance'') of Boeing Service Bulletin 757-
54-0031, Revision 4, dated November 11, 1999: Perform a third eddy 
current inspection (bolt hole inspection) to detect cracking of the 
two fastener holes in the lower spar chord, in accordance with Part 
II of the Accomplishment Instructions of the service bulletin.

Fourth Bolt Hole Inspection

    (j) If, after accomplishment of the inspection required by 
paragraph (i) of this AD, paragraph (m) of this AD has not yet been 
accomplished: When the airplane has reached the flight cycle 
threshold as defined by the flight cycle threshold formula on page 
9, Paragraph 1.E. (``Compliance'') of Boeing Service Bulletin 757-
54-0031, Revision 4,

[[Page 8079]]

dated November 11, 1999; perform a fourth eddy current inspection 
(bolt hole inspection) to detect cracking of the two fastener holes 
in the lower spar chord, in accordance with Part II of the 
Accomplishment Instructions of the service bulletin.

Follow-On Actions

    (k) If no cracking is found during any inspection required by 
paragraph (d), (i), or (j) of this AD, prior to further flight, 
increase the diameter of the holes by the dimensions specified in 
the Accomplishment Instructions of Boeing Service Bulletin 757-54-
0031, Revision 2, dated December 19, 1996, or Revision 4, dated 
November 11, 1999, and install new fasteners in accordance with the 
service bulletin.
    (l) If any cracking is found during any inspection required by 
paragraph (d), (h), (i), or (j) of this AD, prior to further flight, 
accomplish paragraph (l)(1), (l)(2), or (l)(3) of this AD, as 
applicable, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 757-54-0031, Revision 2, dated December 19, 
1996, or Revision 4, dated November 11, 1999.
    (1) If the cracking can be removed by increasing the diameter of 
the hole in accordance with the service bulletin: Increase the 
diameter of the hole by the dimensions specified in the 
Accomplishment Instructions of the service bulletin, and install new 
fasteners in accordance with the service bulletin.
    (2) If the cracking cannot be removed by increasing the diameter 
of the hole in accordance with the Accomplishment Instructions of 
the service bulletin, but the cracking is within the limits 
specified in the service bulletin: Install the repair in accordance 
with the service bulletin. No further action is required by 
paragraph (d) of this AD.
    (3) If the cracking is outside the limits specified in the 
service bulletin: Replace the lower spar chord with a new or 
serviceable chord in accordance with a method approved by the 
Manager, Seattle ACO.

Optional Terminating Modification

    (m) Accomplishment of the modification of the nacelle strut and 
wing structure as required by AD 99-24-07, amendment 39-11431, 
constitutes terminating action for the requirements of this AD.

Alternative Methods of Compliance

    (n) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (o) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (p) Except as provided by paragraphs (c) and (l)(3) of this AD, 
the required actions shall be done in accordance with Boeing Service 
Bulletin 757-54-0031, Revision 2, dated December 19, 1996; or Boeing 
Service Bulletin 757-54-0031, Revision 4, dated November 11, 1999; 
as applicable.
    (1) The incorporation by reference of Boeing Service Bulletin 
757-54-0031, Revision 4, dated November 11, 1999, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Service Bulletin 
757-54-0031, Revision 2, dated December 19, 1996, was approved 
previously by the Director of the Federal Register as of March 28, 
1997 (62 FR 11760, March 13, 1997).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (q) This amendment becomes effective on March 5, 2001.

    Issued in Renton, Washington, on January 18, 2001.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-2111 Filed 1-26-01; 8:45 am]
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