[Federal Register Volume 59, Number 52 (Thursday, March 17, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-6210]


[[Page Unknown]]

[Federal Register: March 17, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-216-AD]

 

Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 series airplanes, that currently requires inspections to 
verify the installation of shear pins, shear pin retainers, and shear 
pin retainer attaching parts in the aft end of the center pylon thrust 
link, and repair, if necessary. That AD also provides an optional 
terminating action, which, if accomplished, would terminate the 
repetitive inspections. That AD was prompted by a report that both 
shear pins that attach the aft end of the center engine pylon thrust 
link to the tail pylon were missing. This action would add inspections 
to verify that the shear pin retainer attaching parts are tightened 
within specified limits; and a terminating modification for those 
inspections. This action would also remove the optional terminating 
action, and expand the applicability of the rule to include additional 
airplanes. The actions specified by the proposed AD are intended to 
prevent structural damage to the engine mount structure, which could 
lead to loss of airplane components.

DATES: Comments must be received by May 10, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 93-NM-216-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, 
CA 90801-1771, Attention: Business Unit Manager, Technical 
Administrative Support, Dept. L51, M.C. 2-98. This information may be 
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, 
Los Angeles Aircraft Certification Office (ACO), 3229 East Spring 
Street, Long Beach, California.

FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-121L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office (ACO), 3229 East Spring Street, 
Long Beach, California 90806-2425; telephone (310) 988-5324; fax (310) 
988-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 93-NM-216-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 93-NM-216-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On October 14, 1992, the FAA issued AD 92-23-03, Amendment 39-8403 
(57 FR 47991, October 21, 1992), applicable to certain McDonnell 
Douglas Model MD-11 series airplanes, to require repetitive visual 
inspections to verify the installation of shear pins, shear pin 
retainers, and shear pin retainer attaching parts at the aft end of the 
center engine (No. 2) pylon thrust link; repair of any discrepancy 
found; and submission of a report of inspection findings to the FAA. 
That AD also provides an optional terminating action for the repetitive 
inspections. That AD was prompted by a report that both shear pins that 
attach the aft end of the center engine pylon thrust link to the tail 
pylon were missing. The requirements of that AD are intended to prevent 
structural damage to the engine mount structure, which could lead to 
loss of airplane components.
    Since the issuance of AD 92-23-03, one operator has reported that, 
during the initial visual inspection conducted in accordance with that 
AD, all bolts and nuts were found installed; however, during a 
subsequent repetitive inspection, one nut and one bolt that attach the 
retainer were missing. If the retainers are missing, the shear pins may 
also be missing and the engine thrust loads will be improperly 
distributed to the airplane structure. This condition, if not 
corrected, could result in structural damage to the engine mount 
structure, which could lead to loss of airplane components.
    The FAA has reviewed and approved McDonnell Douglas MD-11 Alert 
Service Bulletin A54-31, Revision 1, dated June 3, 1993. This service 
bulletin revision adds procedures for performing repetitive inspections 
to verify that the shear pin retainer attaching parts are tightened 
within specific limits. This service bulletin revision also describes 
procedures for replacement of the existing retainer and attaching parts 
with a new retainer and attaching parts. Incorporation of this 
replacement eliminates the need for repetitive visual inspections and 
repetitive tightness verifications. The effectivity listing of this 
service bulletin revision includes 34 additional airplanes identified 
as being subject to the addressed unsafe condition.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 92-23-03 to continue to require 
repetitive visual inspections to verify the installation of the shear 
pins, the shear pin retainers, and the shear pin retainer attaching 
parts in the aft end of the center engine (No. 2) pylon thrust link. 
The proposed AD would add repetitive inspections to verify that the 
shear pin retainer attaching parts are tightened within specified 
limits. If any shear pin, shear pin retainer, or shear pin retainer 
attaching part is missing during any inspection, this proposal would 
continue to require repair in accordance with a method approved by the 
FAA. The ``optional terminating action'' provided by AD 92-23-03, which 
consists of a one-time verification for tightness of the nuts of the 
four shear pin retainer attaching bolts, would no longer be provided in 
the proposed rule.
    The proposed AD would also require eventual replacement of the 
existing retainer and attaching parts with a new retainer and attaching 
parts. When accomplished, this replacement would be considered 
terminating action for the currently required repetitive visual 
inspections and the proposed repetitive verifications of tightness. The 
actions would be required to be accomplished in accordance with the 
revised alert service bulletin described previously.
    This proposal would also require that operators submit a report to 
the FAA of any discrepancy found during any inspection.
    Additionally, this proposal would expand the applicability of the 
rule to include additional airplanes that have been identified as being 
subject to the addressed unsafe condition.
    There are approximately 94 Model MD-11 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 42 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 16 work hours per airplane to accomplish 
the proposed actions and that the average labor rate is $55 per work 
hour. Required parts would be provided at no cost to operators. Based 
on these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $36,960, or $880 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8403 (57 FR 
47991, October 21, 1992), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 93-NM-216-AD. Supersedes AD 92-23-03, 
Amendment 39-8403.

    Applicability: Model MD-11 series airplanes; as listed in 
McDonnell Douglas MD-11 Alert Service Bulletin A54-31, dated 
September 17, 1992, and McDonnell Douglas MD-11 Alert Service 
Bulletin A54-31, Revision 1, dated June 3, 1993; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously. -
    To prevent structural damage to the engine mount structure, 
which could lead to loss of airplane components, accomplish the 
following:
    (a) For airplanes listed in McDonnell Douglas MD-11 Alert 
Service Bulletin A54-31, dated September 17, 1992: Within 15 days 
after November 5, 1992 (the effective date of AD 92-23-03, Amendment 
39-8403), unless previously accomplished within the last 30 days, 
perform a visual inspection of the thrust link of the center engine 
forward mount to verify installation of the shear pins, the shear 
pin retainers, and the shear pin retainer attaching parts in 
accordance with McDonnell Douglas MD-11 Alert Service Bulletin A54-
31, dated September 17, 1992, or Revision 1, dated June 3, 1993.
    (1) If shear pins, shear pin retainers, and shear pin retainer 
attaching parts are installed, repeat the inspection required by 
paragraph (a) of this AD thereafter at intervals not to exceed 60 
days in accordance with the service bulletin until accomplishment of 
paragraph (d) of this AD.
    (2) If any shear pin, shear pin retainer, or shear pin retainer 
attaching part is missing, prior to further flight, repair in 
accordance with a method approved by the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate. Repeat the inspection required by paragraph (a) of this 
AD thereafter at intervals not to exceed 60 days in accordance with 
the service bulletin until accomplishment of paragraph (d) of this 
AD.
    (b) For airplanes listed in McDonnell Douglas MD-11 Alert 
Service Bulletin A54-31, Revision 1, dated June 3, 1993, and not 
subject to the requirements of paragraph (a) of this AD: Within 15 
days after the effective date of this AD, unless previously 
accomplished within the last 30 days, perform a visual inspection of 
the thrust link of the center engine forward mount to verify 
installation of the shear pins, the shear pin retainers, and the 
shear pin retainer attaching parts in accordance with McDonnell 
Douglas MD-11 Alert Service Bulletin A54-31, Revision 1, dated June 
3, 1993.
    (1) If shear pins, shear pin retainers, and shear pin retainer 
attaching parts are installed, repeat the inspection required by 
paragraph (b) of this AD thereafter at intervals not to exceed 60 
days in accordance with the service bulletin until accomplishment of 
paragraph (d) of this AD.
    (2) If any shear pin, shear pin retainer, or shear pin retainer 
attaching part is missing, prior to further flight, repair in 
accordance with a method approved by the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate. Repeat the inspection required by paragraph (b) of this 
AD thereafter at intervals not to exceed 60 days in accordance with 
the service bulletin until accomplishment of paragraph (d) of this 
AD.
    (c) Within 18 months after the effective date of this AD, verify 
that the tightness of the shear pin retainer attaching parts is 
within the limits specified in accordance with McDonnell Douglas MD-
11 Alert Service Bulletin A54-31, Revision 1, dated June 3, 1993. 
Repeat the verification required by paragraphs (c) of this AD 
thereafter at intervals not to exceed 18 months in accordance with 
the service bulletin until accomplishment of paragraph (d) of this 
AD.
    (d) Within 3 years after the effective date of this AD, replace 
the existing retainer and bolts with safety wire with a new retainer 
and new bolts with safety wire in accordance with McDonnell Douglas 
MD-11 Alert Service Bulletin A54-31, Revision 1, dated June 3, 1993. 
Accomplishment of this replacement constitutes terminating action 
for the repetitive actions required by paragraphs (a), (b) and (c) 
of this AD.
    (e) Within 15 days after detecting any discrepancy during any 
inspection or verification action required by this AD, submit a 
report of the inspection results to the Manager, Los Angeles ACO, 
FAA, Transport Airplane Directorate, 3229 East Spring Street, Long 
Beach, California 90806-2425; fax (310) 988-5210. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (f) 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, Los Angeles ACO, FAA, Transport 
Airplane Directorate. Operators shall submit their requests through 
an appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

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

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

    Issued in Renton, Washington, on March 11, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-6209 Filed 3-16-94; 8:45 am]
BILLING CODE 4910-13-U
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-05-AD]

Airworthiness Directives; Boeing Model 747 Series Airplanes 
Equipped With Pratt & Whitney JT9D-3 or JT9D-7 Series Engines, 
Excluding JT9D-70 Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing Model 747 series 
airplanes. This proposal would require inspections of the inboard and 
outboard strut chords, stiffeners, and web to detect cracks and loose 
fasteners; repair of the chords, stiffeners, or web, if necessary; and 
replacement of any loose fastener. This proposal is prompted by reports 
of fatigue cracks and loose fasteners found in the forward lower spar 
web of the inboard strut on Model 747 series airplanes equipped with 
Pratt & Whitney JT9D-3 and JT9D-7 series engines. The actions specified 
by the proposed AD are intended to prevent separation of the strut from 
the wing of the airplane due to fatigue cracking.

DATES: Comments must be received by May 10, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-05-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9 a.m. and 3 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (206) 227-2776; fax (206) 227-1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 94-NM-05-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 94-NM-05-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received six reports of fatigue cracks and one report 
of loose fasteners found in the forward lower spar web of the inboard 
strut on Model 747 series airplanes equipped with Pratt & Whitney JT9D-
3 and JT9D-7 series engines. The cracks were found in the area under 
the stiffeners and baffle and along the web chord. The airplanes on 
which these cracks were found had accumulated between 6,451 and 18,350 
flight cycles and between 17,797 and 83,960 flight hours. All cracks 
reported have been found on the web of the inboard strut.
    During investigation of a recent in-flight engine loss, a similar 
crack of approximately two inches in length was found on the forward 
lower spar web. Although the in-inflight engine loss incident is still 
under investigation, the crack in the web was determined to be a 
contributing cause of the accident.
    Cracking in the forward lower spar web of the inboard strut could 
reduce the lateral strength of the strut. This condition, if not 
detected and corrected in a timely manner, could result in separation 
of the strut from the wing of the airplane due to fatigue cracking.
    Although all cracks reported were found on the web of the inboard 
strut, given standard design tolerances, little difference exists 
between the thickness of the web of the inboard strut (0.025 inch) and 
that of the outboard strut (0.032 inch). Additionally, the inboard and 
outboard webs are similar in configuration and loading environments. 
For these reasons, the FAA finds that the outboard strut web is subject 
to the same unsafe condition as the inboard strut web.
    The FAA has reviewed and approved Boeing Service Bulletin 747-54-
2160, dated September 9, 1993, that describes procedures for repetitive 
detailed visual inspections of the inboard strut chords, stiffeners, 
and web to detect cracks and loose fasteners; repair of the chords, 
stiffeners, or web, if necessary; and replacement of any loose fastener 
found. These same procedures are effective for inspecting the outboard 
strut chord.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require repetitive detailed visual inspections of the 
inboard and outboard strut chords, stiffeners, and web to detect cracks 
and loose fasteners; repair of the chords, stiffeners, or web, if 
necessary; and replacement of any loose fastener. The actions would be 
required to be accomplished in accordance with the procedures specified 
in the service bulletin described previously.
    This is considered to be interim action. The manufacturer has 
advised that it is currently developing a modification program for the 
engine strut that will positively address the unsafe condition 
addressed by this AD. Once this modification program is developed, 
approved, and available, the FAA may consider additional rulemaking.
    There are approximately 380 Model 747 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 140 
airplanes of U.S. registry would be affected by this proposed AD, that 
it would take approximately 22 work hours per airplane to accomplish 
the proposed actions, and that the average labor rate is $55 per work 
hour. Based on these figures, the total cost impact of the proposed AD 
on U.S. operators is estimated to be $169,400, or $1,210 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Boeing: Docket 94-NM-05-AD.

    Applicability: Model 747 series airplanes equipped with Pratt & 
Whitney JT9D-3 or JT9D-7 series engines, excluding JT9D-70 series 
engines; line numbers 001 through 510 inclusive; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent separation of the strut from the wing of the airplane 
due to fatigue cracking, accomplish the following:
    (a) Perform a detailed visual inspection of the inboard and 
outboard strut forward lower spar chords, stiffeners, and web to 
detect cracks and loose fasteners, in accordance with the procedures 
described in Boeing Service Bulletin 747-54-2160, dated September 9, 
1993, at the time specified in paragraph (a)(1), (a)(2), or (a)(3) 
of this AD, as applicable. Repeat this inspection thereafter at 
intervals not to exceed 2,000 landings or 8,000 hours time-in-
service, whichever occurs first.
    (1) For airplanes that have accumulated less than 6,000 total 
landings as of the effective date of this AD: Perform the initial 
inspection at the later of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Prior to the accumulation of 6,000 total landings on the 
strut. Or
    (ii) Within 8 months after the effective date of this AD.
    (2) For airplanes that have accumulated 6,000 or more total 
landings, but less than 15,000 total landings, as of the effective 
date of this AD: Perform the initial inspection within 6 months 
after the effective date of this AD.
    (3) For airplanes that have accumulated 15,000 or more total 
landings as of the effective date of this AD: Perform the initial 
inspection within 4 months after the effective date of this AD.
    (b) If any crack is found during any inspection required by 
paragraph (a) of this AD, prior to further flight, repair in 
accordance with procedures specified in Chapter 54-10-03 of the 747 
Structural Repair Manual.
    (c) If any loose fastener is found during any inspection 
required by paragraph (a) of this AD, prior to further flight, 
replace the fastener in accordance with procedures specified in 
Chapter 51-30-02 of the 747 Structural Repair Manual.
    (d) 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, Transport Airplane Directorate. 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: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

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

    Issued in Renton, Washington, on March 11, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-6210 Filed 3-16-94; 8:45 am]
BILLING CODE 4910-13-U