AD 2001-23-15

[Federal Register Volume 67, Number 3 (Friday, January 4, 2002)]
[Rules and Regulations]
[Pages 489-491]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-84]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-02-AD; Amendment 39-12514; AD 2001-23-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Boeing Model 747 
series airplanes. That AD currently requires repetitive detailed visual 
inspections to find discrepancies of the installation of the midspar 
fuse pins of the inboard and outboard struts, and follow-on actions, if 
necessary. That AD also mandates accomplishment of a terminating 
modification. This document corrects the omission of the phrase 
``amendment 39-12514'' from the first line of the AD. This correction 
is necessary to ensure that the amendment number is stated at the 
beginning of the AD.

DATES: Effective December 31, 2001.
    The incorporation by reference of Boeing Service Bulletin 747-
54A2206, Revision 2, dated May 17, 2001, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
December 31, 2001 (66 FR 58913, November 26, 2001).
    The incorporation by reference of Boeing Service Bulletin 747-
54A2206, Revision 1, dated February 22, 2001, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of March 21, 2001 (66 FR 13424, March 6, 2001).

FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2771; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: On November 15, 2001, the Federal Aviation 
Administration (FAA) issued AD 2001-23-15, amendment 39-12514 (66 FR 
58913, November 26, 2001), which applies to certain Boeing Model 747 
series airplanes. That AD requires repetitive detailed visual 
inspections to find discrepancies of the installation of the midspar 
fuse pins of the inboard and outboard struts, and follow-on actions, if 
necessary. That AD also provides for an optional terminating 
modification for the repetitive inspections. The actions required by 
that AD are intended to find and fix discrepancies of the installation 
of the midspar fuse pins, which could result in loss of the secondary 
retention capability of the fuse pins, migration of the fuse pins, and 
consequent loss of the strut and engine from the airplane.

Need for the Correction

    The FAA has determined that a correction to AD 2001-23-15 is 
necessary. The correction will add the amendment number (amendment 39-
12514) to the first line of the AD. That number was inadvertently 
omitted from the final rule, as published.

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment

[[Page 490]]

to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).
    The AD is reprinted in its entirety for the convenience of affected 
operators. The effective date of the AD remains December 31, 2001.
    Since this action only corrects the inadvertent omission of the 
amendment number from the first line of the AD, it has no adverse 
economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

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

Adoption of the Correction

    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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2001-23-15  Boeing: Amendment 39-12514. Docket 2001-NM-02-AD. 
Supersedes AD 2001-05-05, amendment 39-12141.

    Applicability: Model 747 series airplanes, line numbers 1 
through 1046 that have accomplished Airworthiness Directives 95-10-
16, 95-13-05, 95-13-06, or 95-13-07; and line numbers 1047 through 
1271 inclusive; 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 (c)(1) 
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 find and fix discrepancies of the installation of the midspar 
fuse pins of the inboard and outboard strut, which could result in 
loss of the secondary retention capability of the fuse pins, 
migration of the fuse pins, and consequent loss of the strut and 
engine from the airplane; accomplish the following:

Restatement of the Requirements of AD 2001-05-05

Inspections/Follow-On Actions

    (a) At the time specified in paragraph (a)(1) or (a)(2) of this 
AD, as applicable: Do a detailed visual inspection to find 
discrepancies (e.g., incorrect thread protrusion, which is less than 
two threads protruding from the nut between the nut and the 
secondary retention washer; incorrect gap between the fuse pin 
primary nut and secondary retention washer; cracked or broken torque 
stripe) of the installation of the midspar fuse pins of the inboard 
and outboard struts, per Figure 2 of Boeing Service Bulletin 747-
54A2206, Revision 1, dated February 22, 2001, or Revision 2, dated 
May 17, 2001.
    (1) For airplanes having the production equivalent of one of the 
AD's listed in Table 1 of this AD: Do the inspection at the later of 
the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this 
AD.
    (i) Before the accumulation of 8,000 total flight hours, or 
within 24 months since manufacture of the airplane, whichever occurs 
first.
    (ii) Within 90 days after March 21, 2001 (the effective date of 
AD 2001-05-05, amendment 39-12141).
    (2) For airplanes modified per one of the AD's listed in Table 1 
of this AD: Do the inspection at the later of the times specified in 
paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. Table 1 follows:

                                 Table 1
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                                                              Amendment
                         AD number                              number
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AD 95-10-16................................................      39-9233
AD 95-13-05................................................      39-9285
AD 95-13-06................................................      39-9286
AD 95-13-07................................................      39-9287
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    (i) Within 8,000 flight hours or 24 months after the 
modification, whichever occurs first.
    (ii) Within 90 days after March 21, 2001.

    Note 2: Where there are differences between the AD and the 
service bulletin, the AD prevails.


    Note 3: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (A) If no discrepancy is found: Repeat the inspection at 
intervals not to exceed 8,000 flight hours or 24 months, whichever 
occurs first, until you do the terminating modification specified in 
paragraph (b) of this AD.
    (B) If any discrepancy is found, and the primary nut has backed 
off and contacts the secondary retention washer: Before further 
flight, do the terminating modification specified in paragraph (b) 
of this AD.
    (C) If any discrepancy is found, and the primary nut does not 
contact the secondary retention washer: Repeat the inspection at 
intervals not to exceed 90 days. Within 18 months after the initial 
finding, or before March 21, 2001, whichever occurs later, do the 
terminating modification specified in paragraph (b) of this AD.

    Note 4: Inspections done prior to the effective date of this AD 
per Boeing Alert Service Bulletin 747-54A2206, dated October 19, 
2000, are acceptable for compliance with the inspections required by 
paragraph (a) of this AD.

New Requirements of this AD

Terminating Action

    (b) Within 6 years after the effective date of this AD: Do the 
terminating modification (replacement of the primary nut of the 
midspar fuse pin, installation of torque strip, a detailed visual 
inspection of the fuse pin threads for damage, and replacement, if 
necessary) per Figure 3 of Boeing Service Bulletin 747-54A2206, 
Revision 1, dated February 22, 2001, or Figure 3 of Boeing Service 
Bulletin 747-54A2206, Revision 2, dated May 17, 2001. Doing this 
modification ends the repetitive inspections required by this AD.

    Note 5: Doing the terminating modification prior to the 
effective date of this AD per Boeing Alert Service Bulletin 747-
54A2206, dated October 19, 2000, is acceptable for compliance with 
the terminating action required by paragraph (b) of this AD.

Alternative Methods of Compliance

    (c)(1) 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 Aircraft Certification 
Office (ACO), FAA. 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.
    (2) Any alternative method of compliance which was approved 
previously in accordance with AD 2001-05-05 is approved for 
compliance with this AD.

    Note 6: 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

    (d) 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

    (e) The actions shall be done in accordance with Boeing Service 
Bulletin 747-54A2206, Revision 1, dated February 22, 2001; or Boeing 
Service Bulletin 747-54A2206, Revision 2, dated May 17, 2001.

[[Page 491]]

    (1) The incorporation by reference of Boeing Service Bulletin 
747-54A2206, Revision 2, dated May 17, 2001, was approved previously 
by the Director of the Federal Register, as of December 31, 2001 (66 
FR 58913, November 26, 2001).
    (2) The incorporation by reference of Boeing Service Bulletin 
747-54A2206, Revision 1, dated February 22, 2001, was approved 
previously by the Director of the Federal Register as of March 21, 
2001 (66 FR 13424, March 6, 2001).
    (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

    (f) This amendment becomes effective on December 31, 2001.

    Issued in Renton, Washington, on December 20, 2001.
Ali Bahrami,
Acting Manager,Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-84 Filed 1-3-02; 8:45 am]
BILLING CODE 4910-13-U