AD Amdt-39-10275

[Federal Register Volume 63, Number 8 (Tuesday, January 13, 1998)]
[Rules and Regulations]
[Pages 1905-1907]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-207]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-90-AD; Amendment 39-10275; AD 98-01-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Industrie Model A320 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Industrie Model A320 series airplanes, 
that requires an inspection to detect

[[Page 1906]]

moisture and migrated bushings of the guide fittings of the safety 
locking pins of the passenger doors, removal of any moisture, 
application of grease, and reinstallation of any migrated bushing. This 
amendment also requires installation of a greasing nipple on the guide 
fitting of the locking pin and on three telescopic rods on the 
passenger doors. This amendment is prompted by reports of difficulty 
opening the passenger doors due to jamming of the locking pin. The 
actions specified by this AD are intended to prevent such jamming of 
the locking pin, which could result in inability to open the passenger 
door. This condition, if not corrected, could impede or delay 
passengers from exiting the airplane during an emergency.

DATES: Effective February 17, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 17, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. 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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Industrie Model 
A320 series airplanes was published in the Federal Register on November 
3, 1995 (60 FR 55811). That action proposed to require a one-time 
inspection to detect moisture and migrated bushings of the guide 
fittings of the upper safety locking pins of the passenger doors, 
removal of any moisture, application of grease, and reinstallation of 
any migrated bushing. That action also proposed to require installation 
of a greasing nipple on the guide fitting of the locking pin and on 
three telescopic rods on the passenger doors.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request to Extend Compliance Time for Installation of Greasing Nipple

    One commenter requests that the compliance time for accomplishing 
the proposed installation of a greasing nipple on the three telescopic 
rods on the passenger door be extended from the proposed 15 months to 
18 months. The commenter states that such an extension will allow the 
installation to be accomplished during a regularly scheduled ``C'' 
check, and thereby eliminate any expenses that would be associated with 
special scheduling. Another commenter requests an explanation as to how 
the 15-month compliance time was established.
    The FAA does not concur with the commenter's request to extend the 
compliance time. In developing an appropriate compliance time for this 
action, the FAA considered the safety implications, parts availability, 
and normal maintenance schedules for timely accomplishment of the 
installation. Further, the proposed compliance time of 15 months was 
arrived with operator, manufacturer, Direction Generale de l'Aviation 
Civile (DGAC) (the airworthiness authority for France), and FAA 
concurrence. In light of this, and in consideration of the amount of 
time that has already passed since issuance of the original notice, the 
FAA has determined that further delay of this final rule is not 
appropriate. However, under the provisions of paragraph (c) of the 
final rule, the FAA may approve requests for adjustments to the 
compliance time if data are submitted to substantiate that such an 
adjustment would provide an acceptable level of safety.

Request to Require Only Rework of Safety Guide Pin Fitting

    One commenter requests that the proposed AD be revised to require 
only rework applicable to the telescopic rods of the passenger door if 
Airbus Industrie Service Bulletin A320-52-1030 has not been 
accomplished. (The proposal requires that actions be accomplished in 
accordance with Airbus Industries Service Bulletin A320-52-1057.) The 
commenter points out that the sliding arming mechanism telescopic rod 
has been the subject of Airbus Industrie Service Bulletin A320-52-1030, 
which describes procedures to detect a corrosion problem. Since 
incorporation of that service bulletin, the commenter states that it 
has not had any discrepancies with any of the telescopic rods that are 
subject to the proposed AD. The FAA does not concur. The FAA finds that 
the procedures specified in Airbus Industrie Service Bulletin A320-52-
1030 do not address the same unsafe condition addressed by this AD 
(i.e., jamming of the locking pin). The FAA has determined that 
accomplishment of the procedures specified in Airbus Industrie Service 
Bulletin A320-52-1057, as proposed, adequately addresses the identified 
unsafe condition by preventing jamming of the locking pin. However, 
under the provisions of paragraph (c) of this AD, operators may apply 
for the approval of an alternative method of compliance, if sufficient 
justification is presented to the FAA.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The FAA estimates that 108 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
airplane (1 work hour per door; 4 doors per airplane) to accomplish the 
required inspection, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the inspection 
required by this AD on U.S. operators is estimated to be $25,920, or 
$240 per airplane.
    The FAA estimates that it will take approximately 40 work hours per 
airplane to accomplish the required installation, and that the average 
labor rate is $60 per work hour. Required parts will be supplied by the 
manufacturer at no cost to operators. Based on these figures, the cost 
impact of the installation on U.S. operators is estimated to be 
$259,200, or $2,400 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

[[Page 1907]]

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 ``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 adding the following new 
airworthiness directive:

98-01-12  Airbus Industrie: Amendment 39-10275. Docket 95-NM-90-AD.

    Applicability: Model A320 series airplanes on which Airbus 
Industrie Modification No. 24389 (Airbus Industrie Service Bulletin 
No. A320-52-1057, dated July 26, 1994) has not been accomplished, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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) 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 jamming of the upper safety locking pin on the 
passenger door, which could result in inability to open the 
passenger door and, consequently, could impede or delay passengers 
from exiting the airplane during an emergency, accomplish the 
following:
    (a) Prior to the accumulation of 450 hours time-in-service after 
one year from the delivery date of the airplane, or within 450 hours 
time-in-service after the effective date of this AD, whichever 
occurs later: Perform an inspection to detect moisture or migrated 
bushings of the guide fittings of the upper safety locking pins on 
each passenger door, in accordance with Airbus Industrie All 
Operators Telex (AOT) 52-06, dated February 4, 1994.
    (1) If any moisture is found in the guide fitting, prior to 
further flight, remove the moisture, dry the guide fitting, fill it 
with low temperature grease, and reinstall the guide fitting with 
bolts, washers, and nuts in accordance with the AOT.
    (2) If any migrated bushing is found, prior to further flight, 
reinstall the bushing using Loctite 672 in accordance with the AOT. 
If the bushing cannot be reinstalled prior to further flight, the 
airplane may be operated without the upper locking pin for an 
additional 50 hours time-in-service or three days after 
accomplishing the inspection, whichever occurs first, provided that 
the requirements specified in paragraphs (a)(2)(i), (a)(2)(ii), and 
(a)(2)(iii) of this AD are accomplished. This compliance time 
applies to each passenger door.
    (i) The connecting rod to the locking shaft shall be removed.
    (ii) The guide fitting shall remain installed.
    (iii) The cavity in the guide fitting (which results from the 
removal of the upper locking pin) shall be covered with high speed 
tape to prevent moisture ingress.
    (b) Within 15 months after the effective date of this AD, 
install a greasing nipple on the guide fitting of the locking pin 
and on three telescopic rods on the passenger doors in accordance 
with Airbus Industrie Service Bulletin No. A320-52-1057, dated July 
26, 1994.
    (c) 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, 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, International 
Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (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.
    (e) The actions shall be done in accordance with Airbus 
Industrie All Operators Telex (AOT) 52-06, dated February 4, 1994, 
and Airbus Industrie Service Bulletin No. A320-52-1057, dated July 
26, 1994. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 94-239-060(B), dated November 9, 1994.

    (f) This amendment becomes effective on February 17, 1998.

    Issued in Renton, Washington, on December 30, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-207 Filed 1-12-98; 8:45 am]
BILLING CODE 4910-13-U