AD Amdt-39-11059

[Federal Register Volume 64, Number 43 (Friday, March 5, 1999)]
[Rules and Regulations]
[Pages 10555-10557]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-5041]



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Federal Register / Vol. 64, No. 43 / Friday, March 5, 1999 / Rules 
and Regulations

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-27-AD; Amendment 39-11059; AD 99-05-11]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Model BAC 1-11 200 
and 400 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 all British Aerospace Model BAC 1-11 200 and 400 
series airplanes, that currently requires repetitive visual inspections 
to detect cracks in the flight deck canopy area, and repair, if 
necessary; and repetitive detailed visual and eddy current inspections 
to detect cracks of the top sill members at station 82.5, and 
replacement of cracked parts with new parts, or repair of the top sill 
members. This amendment continues to require detailed visual and eddy 
current inspections to detect cracks of the top sill members at station 
82.5. This amendment also adds a requirement for a one-time inspection 
to determine the type of fasteners installed in certain holes of the 
joint strap installation, and replacement of rivets with bolts, if 
necessary. This amendment is prompted by the issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified by this AD are intended to detect and 
correct cracking in the flight deck canopy area, which could result in 
reduced structural integrity of the flight deck frame and adjacent 
fuselage structure.

DATES: Effective April 9, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 9, 1999.
    The incorporation by reference of British Aerospace Alert Service 
Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of April 22, 1996 (61 FR 11534, March 21, 1996).

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace, Service Support, Airbus Limited, P.O. 
Box 77, Bristol BS99 7AR, England. 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-06-07, 
amendment 39-9544 (61 FR 11534, March 21, 1996), which is applicable to 
all British Aerospace Model BAC 1-11 200 and 400 series airplanes, was 
published in the Federal Register on January 6, 1999 (64 FR 785). The 
action proposed to continue to require detailed visual and eddy current 
inspections to detect cracks of the top sill members at station 82.5, 
and replacement of cracked parts with new parts, or repair of the top 
sill members. The action also proposed to add a requirement for a one-
time inspection to determine the type of fasteners installed in certain 
holes of the joint strap installation, and replacement of rivets with 
bolts, if necessary.

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 42 airplanes of U.S. registry that will be 
affected by this AD.
    The actions that are currently required by AD 96-06-07, and 
retained in this AD, take approximately 19 work hours per airplane to 
accomplish (including access and close), 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 
$47,880, or $1,140 per airplane, per inspection cycle.
    The new inspection that is required in this AD action will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the new inspection required by this AD on U.S. operators is 
estimated to be $2,520, or $60 per airplane.
    Should an operator be required to accomplish the necessary 
replacement of rivets with bolts, it will take approximately 3 work 
hours per airplane to accomplish the replacement, at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
any necessary replacement of rivets is estimated to be $180 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.

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a

[[Page 10556]]

``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 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 39-9544 (61 FR 
11534, March 21, 1996), and by adding a new airworthiness directive 
(AD), amendment 39-11059, to read as follows:

99-05-11  British Aerospace Airbus Limited (Formerly British 
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft 
Group): Amendment 39-11059. Docket 98-NM-27-AD. Supersedes AD 96-06-
07, Amendment 39-9544.

    Applicability: All Model BAC 1-11 200 and 400 series airplanes, 
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 (d) 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 prevent reduced structural integrity of the flight deck frame 
and adjacent fuselage structure, accomplish the following:
    (a) Perform a detailed visual inspection to detect cracks of the 
top sill joint strap at station 82.5, of the frame at station 113, 
and of the frame at station 160.5 (left-hand side only) between 
stringers 13 and 15; and an eddy current inspection to detect cracks 
of the top sill members at station 82.5. Perform these inspections 
in accordance with British Aerospace Alert Service Bulletin 53-A-
PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 
1996; or Issue 5, dated April 18, 1997; at the time specified in 
paragraph (a)(1) or (a)(2) of this AD, as applicable. After the 
effective date of this AD, only Issue 5 shall be used.
    (1) For airplanes operating at a maximum cabin differential 
pressure not exceeding 7.5 pounds per square inch (psi): Perform the 
inspections at the later of the times specified in paragraphs 
(a)(1)(i) and (a)(1)(ii) of this AD. Thereafter, repeat these 
inspections at intervals not to exceed 5,000 landings or 7,500 hours 
time-in-service, whichever occurs first.
    (i) Prior to the accumulation of 20,000 total landings. Or
    (ii) Within 1,200 landings or 12 months after April 22, 1996 
(the effective date of AD 96-06-07, amendment 39-9544), whichever 
occurs later.
    (2) For airplanes operating at a maximum cabin differential 
pressure greater than 7.5 psi, but not exceeding 8.2 psi, including 
those airplanes having incorporated British Aerospace Airbus Limited 
Modification PM3187: Perform the inspections at the later of the 
times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. 
Thereafter, repeat these inspections at intervals not to exceed 
3,500 landings or 5,250 hours time-in-service, whichever occurs 
first.
    (i) Prior to the accumulation of 14,000 total landings. Or
    (ii) Within 800 landings or 12 months after April 22, 1996, 
whichever occurs later.

    Note 2: British Aerospace Airbus Limited Modification PM3187 
increases the cabin differential pressure from the normal 7.5 psi to 
8.2 psi. If Modification PM3187 has been incorporated on the 
airplane, that airplane is considered to be subject to the 
requirements of paragraph (a)(2) of this AD.

    (b) Concurrent with the next detailed visual inspection 
performed after the effective date of this AD in accordance with 
paragraph (a) of this AD, perform a one-time visual inspection to 
determine the type of fasteners installed in the two hole locations 
specified in Figure 2 of British Aerospace Alert Service Bulletin 
53-A-PM5994, Issue 5, dated April 18, 1997.
    (1) If bolts are found installed in the two hole locations 
specified in Figure 2 of the alert service bulletin: Prior to 
further flight, remove the bolts and perform the eddy current 
inspection specified in paragraph (a) of this AD to detect cracking 
of the top sill members at station 82.5, in accordance with the 
alert service bulletin. Repeat the detailed visual and eddy current 
inspections thereafter as specified in paragraph (a)(1) or (a)(2) of 
this AD, as applicable; in accordance with the alert service 
bulletin.
    (i) If no cracking is detected, prior to further flight, 
reinstall the bolts.
    (ii) If any cracking is detected, prior to further flight, 
repair in accordance with paragraph (c) of this AD, and reinstall 
the bolts.
    (2) If rivets are found installed in the two hole locations 
specified in Figure 2 of the alert service bulletin: Prior to 
further flight, remove the rivets, and perform the eddy current 
inspection specified in paragraph (a) of this AD to detect cracking 
of the top sill members at station 82.5, in accordance with the 
alert service bulletin. Repeat the detailed visual and eddy current 
inspections thereafter as specified in paragraph (a)(1) or (a)(2) of 
this AD, as applicable; in accordance with the alert service 
bulletin.
    (i) If no cracking is detected, prior to further flight, 
oversize the holes specified in Figure 2 of the alert service 
bulletin, and install bolts in place of the rivets.
    (ii) If any cracking is detected, prior to further flight, 
repair in accordance with paragraph (c) of this AD, oversize the 
holes specified in Figure 2 of the alert service bulletin, and 
install bolts in place of the rivets.

    Note 3: As specified in British Aerospace Alert Service Bulletin 
53-A-PM5994, Issue 4, dated August 23, 1996, and Issue 5, dated 
April 18, 1997, the procedures for the eddy current inspection 
necessitate removal of the bolts from the holes specified in Figure 
2 of the alert service bulletin.

    (c) If any crack is found during any inspection required by 
paragraph (a) or (b) of this AD, prior to further flight, accomplish 
the requirements of paragraph (c)(1), (c)(2), or (c)(3) of this AD, 
as applicable.
    (1) For cracking of the joint strap, doubler, or angle at the 
sill joint at station 82.5: Replace the cracked part with a new part 
in accordance with British Aerospace Alert Service Bulletin 53-A-
PM5994, Issue 3, dated April 8, 1993; Issue 4, dated August 23, 
1996; or Issue 5, dated April 18, 1997. After the effective date of 
this AD, only Issue 5 shall be used.
    (2) For cracking of the frame at station 113: Repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the Civil Aviation Authority (or its delegated agent).
    (3) For cracking of the frame at station 160.5: Repair in 
accordance with the Structural Repair Manual, as specified in 
British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 3, dated 
April 8, 1993; Issue 4, dated August 23, 1996; or Issue 5, dated 
April 18, 1997. After the effective date of this AD, only Issue 5 
shall be used.

Alternative Methods of Compliance

    (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, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.


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    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (e) 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

    (f) The inspections, removal, and replacement shall be done in 
accordance with British Aerospace Alert Service Bulletin 53-A-
PM5994, Issue 3, dated April 8, 1993; British Aerospace Alert 
Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; or 
British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated 
April 18, 1997.
    (1) The incorporation by reference of British Aerospace Alert 
Service Bulletin 53-A-PM5994, Issue 4, dated August 23, 1996; and 
British Aerospace Alert Service Bulletin 53-A-PM5994, Issue 5, dated 
April 18, 1997, 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 British Aerospace Alert 
Service Bulletin 53-A-PM5994, Issue 3, dated April 8, 1993, as 
listed in the regulations, was approved previously by the Director 
of the Federal Register as of April 22, 1996 (61 FR 11534, March 21, 
1996).
    (3) Copies may be obtained from British Aerospace, Service 
Support, Airbus Limited, P.O. Box 77, Bristol BS99 7AR, England. 
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.
    (g) This amendment becomes effective on April 9, 1999.

    Issued in Renton, Washington, on February 23, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-5041 Filed 3-4-99; 8:45 am]
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