[Federal Register Volume 60, Number 73 (Monday, April 17, 1995)]
[Proposed Rules]
[Pages 19175-19179]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-9345]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-185-AD]


Airworthiness Directives; British Aerospace Model BAC 1-11-200 
and -400 Series Airplanes

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 British Aerospace Model 
BAC 1-11-200 and -400 series airplanes. This proposal would require 
various inspections to detect discrepancies of fuselage frames at 
certain stations, and correction of discrepancies; and rework to limit 
the maximum differential operating pressure of the fuselage. This 
proposal would also require eventual modification of fuselage frames at 
certain stations, which would terminate the repetitive inspection 
requirements. This proposal is prompted by reports of fatigue cracking 
in certain fuselage frames in the vicinity of the passenger door at 
floor level due to fatigue-related stress. The actions specified by the 
proposed AD are intended to prevent such fatigue-related cracking, 
which could result in reduced structural integrity of the fuselage 
pressure vessel and possible decompression of the pressurized cabin.

DATES: Comments must be received by May 26, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-185-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol 
BS99 7AR, England. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

[[Page 19176]] FOR FURTHER INFORMATION CONTACT: William Schroeder, 
Aerospace Engineer, Standardization Branch, ANM-113, FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (206) 227-2148; fax (206) 227-1320.

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-185-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-185-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Civil Aviation Authority (CAA), which is the airworthiness 
authority for the United Kingdom, recently notified the FAA that an 
unsafe condition may exist on certain British Aerospace Model BAC 1-11-
200 and -400 series airplanes. The CAA advises that reports have been 
received of fatigue cracking in frames 178 and 213.5 in the vicinity of 
the passenger door at floor level. Investigation revealed that such 
cracking was caused by fatigue-related stress. Such fatigue-related 
cracking, if not detected and corrected in a timely manner, could 
result in reduced structural integrity of the fuselage pressure vessel 
and possible decompression of the pressurized cabin.
    British Aerospace has issued Alert Service Bulletin 53-A-PM5993, 
Issue 1, dated January 11, 1993. This alert service bulletin describes 
procedures for various repetitive inspections to detect structural 
discrepancies of the various structural configurations of the fuselage 
frames at stations 178 and 213.5, and correction of any discrepancy. 
This alert service bulletin also describes procedures for rework to 
limit the maximum differential operating pressure of the fuselage. 
Additionally, this alert service bulletin describes procedures for 
modification of fuselage frames at stations 178 and 213.5, which would 
eliminate the need for the repetitive inspections. For airplanes 
unrepaired or not reinforced by repair and operated at cabin 
pressurization differentials not exceeding 7.5 pounds per square inch 
(psi), the alert service bulletin describes procedures for the 
installation of terminating Modification PM5993 at 55,000 total 
landings. This modification introduces reinforcing structure to the 
subject area. The CAA classified this alert service bulletin as 
mandatory.
    These airplane models are manufactured in the United Kingdom and 
are type certificated for operation in the United States under the 
provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Pursuant 
to this bilateral airworthiness agreement, the CAA has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would require various repetitive 
inspections to detect structural discrepancies of the various 
structural configurations of the fuselage frames at stations 178 and 
213.5, and correction of any discrepancy. The proposed AD would also 
require rework to limit the maximum differential operating pressure of 
the fuselage. Additionally, this proposed AD would require eventual 
modification of fuselage frames at stations 178 and 213.5, which would 
constitute terminating action for the repetitive inspection 
requirements. The actions would be required to be accomplished in 
accordance with the alert service bulletin described previously.
    The requirements of this proposed AD would differ from certain 
actions recommended in the referenced alert service bulletin. 
Specifically, for airplanes unrepaired or not reinforced by repair and 
operated at cabin pressurization differentials not exceeding 7.5 psi, 
the proposed AD would require installation of terminating Modification 
PM5993 prior to the accumulation of 85,000 total landings, rather than 
55,000 total landings as indicated in the alert service bulletin. The 
higher threshold of 85,000 landings for modification has been 
recommended by the Airworthiness Assurance Working Group (AAWG), 
sponsored by the Air Transport Association (ATA) of America, the 
Aerospace Industries Association (AIA), and the FAA. In selecting that 
threshold, the AAWG considered the type of cracking involved, the 
impact such cracking would have on the adjacent structure, and service 
history of cracking in the subject area. The AAWG has recommended, and 
the FAA concurs, that safety will not be compromised if Modification 
PM5993 is installed prior to the accumulation of 85,000 total landings.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been included in this notice to clarify this requirement.
    The FAA estimates that 31 airplanes of U.S. registry would be 
affected by this proposed AD.
    It would take approximately 8 work hours per airplane to accomplish 
the proposed inspection at an average labor rate of $60 per work hour. 
Based on these figures, the total cost impact of the inspection 
proposed by this AD on U.S. operators is estimated to be $14,880, or 
$480 per airplane.
    It would take approximately 80 work hours per airplane to 
accomplish the [[Page 19177]] proposed modification at an average labor 
rate of $60 per work hour. Required parts would cost approximately 
$2,000 per airplane. Based on these figures, the total cost impact of 
the modification proposed by this AD on U.S. operators is estimated to 
be $210,800, or $6,800 per airplane.
    Based on above figures, the total cost impact of the proposed 
inspection and modification on U.S. operators is estimated to be 
$225,680, or $7,280, 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 
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. 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:

British Aerospace Airbus Limited (Formerly British Aerospace 
Commercial Aircraft Limited, British Aerospace Aircraft Group): 
Docket 94-NM-185-AD.

    Applicability: Model BAC 1-11-200 and -400 series airplanes on 
which British Aerospace Modifications PM5445 and PM5713 have not 
been installed, 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 use the authority 
provided in paragraph (h) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue-related cracking in fuselage frames at 
stations 178 and 213.5 in the vicinity of the passenger door at 
floor level, which could result in reduced structural integrity of 
the fuselage pressure vessel and possible decompression of the 
pressurized cabin, accomplish the following:
    (a) For airplanes unrepaired or not reinforced by repair on 
frames 178 and 213.5, in the area between stringers 25L and 27L: 
Accomplish paragraphs (a)(1), (a)(2), (a)(3), and (a)(4) of this AD, 
in accordance with British Aerospace Airbus Limited Alert Service 
Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.1 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.1 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (a)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.1 of the Accomplishment 
Instructions of the alert service bulletin.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.1.5 or 2.1.10, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frame at stations 178 
and 213.5 in accordance with paragraph 2.1.5 or 2.1.10, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (a)(1) and 
(a)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 pounds per 
square inch (psi), in accordance with the alert service bulletin.
    (b) For airplanes on which Structural Repair Manual, figure 76, 
repair in-situ has been acccomplished: Accomplish paragraphs (b)(1), 
(b)(2), (b)(3), and (b)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.2 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.2 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (b)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.2 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.2.6 or 2.2.9, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frame at stations 178 
and 213.5 in accordance with paragraph 2.2.6 or 2.2.9, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (b)(1) and 
(b)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (c) For airplanes on which Structural Repair Manual, figure 87, 
repair has been accomplished: Accomplish paragraphs (c)(1), (c)(2), 
(c)(3), and (c)(4) of this AD, in accordance with British Aerospace 
Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 1, dated 
January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.3 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
[[Page 19178]] at intervals specified in paragraph 2.3 of the 
Accomplishment Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (c)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.3 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.3.5 or 2.3.8, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.3.5 or 2.3.8, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (c)(1) and 
(c)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (d) For airplanes on which Structural Repair Manual, figure 110 
or 111, repair has been accomplished: Accomplish paragraphs (d)(1), 
(d)(2), (d)(3), and (d)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.4 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.4 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (d)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with a method approved by the Manager, 
Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.4.5 or 2.4.8, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.4.5 or 2.4.8, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (d)(1) and 
(d)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (e) For airplanes on which Structural Repair Manual, figure 76, 
reinforcement has been accomplished: Accomplish paragraphs (e)(1), 
(e)(2), (e)(3), (e)(4), and (e)(5) of this AD, in accordance with 
British Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, 
Issue 1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.5 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.5 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (e)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.5 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.5.5 or 2.5.10, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.5.5 or 2.5.10, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (e)(1) and 
(e)(2) of this AD.
    (4) For airplanes operated at a cabin maximum pressure 
differential in excess of 7.5 psi, prior to the threshold times 
specified in Table C of the service bulletin, replace the 
reinforcements accomplished in accordance with the Structural Repair 
Manual, figure 76, with reinforcements accomplished in accordance 
with Structural Repair Manual 53-02-00, figure 110 or 111, as 
specified in the alert service bulletin.
    (5) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (f) For airplanes on which Structural Repair Manual, figure 87, 
reinforcement has been accomplished: Accomplish paragraphs (f)(1), 
(f)(2), (f)(3), and (f)(4) of this AD, in accordance with British 
Aerospace Airbus Limited Alert Service Bulletin 53-A-PM5993, Issue 
1, dated January 11, 1993.
    (1) Perform the initial inspection prior to the compliance time 
specified in paragraph 2.6 of the Accomplishment Instructions of the 
alert service bulletin or within 12 months after the effective date 
of this AD, whichever occurs later. Repeat the inspection thereafter 
at intervals specified in paragraph 2.6 of the Accomplishment 
Instructions of the alert service bulletin.
    (2) If any discrepancy is found during any inspection required 
by paragraph (f)(1) of this AD, prior to further flight, correct the 
discrepancy in accordance with paragraph 2.6 of the Accomplishment 
Instructions of the alert service bulletin; or in accordance with a 
method approved by the Manager, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate.
    (3) Prior to the accumulation of the total number of landings 
specified in paragraph 2.6.6 or 2.6.9, as applicable, of the 
Accomplishment Instructions of the alert service bulletin or within 
12 months after the effective date of this AD, whichever occurs 
later, modify the structure of the fuselage frames at stations 178 
and 213.5 in accordance with paragraph 2.6.6 or 2.6.9, as 
applicable, of the Accomplishment Instructions of the alert service 
bulletin. Accomplishment of this modification constitutes 
terminating action for the requirements of paragraphs (f)(1) and 
(f)(2) of this AD.
    (4) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with the alert service bulletin.
    (g) For airplanes on which repairs other than those described in 
the Structural Repair Manual have been accomplished on frames 178 
and 213.5, in the area between stringers 25L and 27L: Accomplish 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
    (1) Within 6 months after the effective date of this AD, submit 
the following for approval to the Manager, Standardization Branch, 
ANM-113, FAA, Transport Airplane Directorate:
    (i) Procedures and schedule for accomplishing the initial and 
repetitive inspections of the fuselage frames at stations 178 and 
213.5; and
    (ii) Schedule for installation of Modification PM5993 or 
Structural Repair Manual, figure 110 and 111, as applicable, at the 
fuselage frames at stations 178 and 213.5.
    (2) Within 6 months after the procedures and schedules are 
approved, revise the FAA-approved maintenance program to include 
these procedures.
    (3) Prior to the accumulation of 55,000 total landings or within 
12 months after the effective date of this AD, whichever occurs 
later, rework the cabin pressurization system to limit the maximum 
differential operating pressure of the fuselage to 7.5 psi, in 
accordance with British Aerospace Airbus Limited Alert Service 
Bulletin 53-A-PM5993, Issue 1, dated January 11, 1993.
    (h) 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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of [[Page 19179]] compliance with this AD, if 
any, may be obtained from the Standardization Branch, ANM-113.

    (i) Special flight permits may be issued in accordance with 
Secs. 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.

    Issued in Renton, Washington, on April 11, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-9345 Filed 4-14-95; 8:45 am]
BILLING CODE 4910-13-U