80_FR_12003 80 FR 11960 - Airworthiness Directives; Airbus Airplanes

80 FR 11960 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 43 (March 5, 2015)

Page Range11960-11963
FR Document2015-04504

We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. This proposed AD would require modification of the pin programming flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. We are proposing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane.

Federal Register, Volume 80 Issue 43 (Thursday, March 5, 2015) 
[Federal Register Volume 80, Number 43 (Thursday, March 5, 2015)]
[Proposed Rules]
[Pages 11960-11963]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-04504]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed 
AD was prompted by a determination that, in specific flight conditions, 
the allowable load limits on the vertical tail plane could be reached 
and possibly exceeded. Exceeding allowable load could result in 
detachment of the vertical tail plane. This proposed AD would require 
modification of the pin programming flight warning computer (FWC) to 
activate the stop rudder input warning (SRIW) logic; and an inspection 
to determine the part numbers of the FWC and the flight augmentation 
computer (FAC), and replacement of the FWC and FAC if necessary. We are 
proposing this AD to prevent detachment of the vertical tail plane and 
consequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by April 20, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email

[[Page 11961]]

[email protected]; Internet http://www.airbus.com. You 
may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0251; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0251; 
Directorate Identifier 2014-NM-200-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2014-0217, dated September 26, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Model A318, A319, 
A320, and Model A321 series airplanes. The MCAI states:

    During design reviews that were conducted following safety 
recommendations related to in-service incidents and one accident on 
another aircraft type, it has been determined that, in specific 
flight conditions, the allowable load limits on the vertical tail 
plane could be reached and possibly exceeded.
    This condition, if not corrected, could lead, in the worst case, 
to detachment of the vertical tail plane in flight and consequent 
loss of the aeroplane.
    To prevent such a possibility, Airbus has developed 
modifications within the flight augmentation computer (FAC) to 
reduce the vertical tail plane stress and to activate a conditional 
aural warning within the flight warning computer (FWC) to further 
protect against pilot induced rudder doublets.
    For the reasons described above, this [EASA] AD requires 
installation and activation of the stop rudder input warning (SRIW) 
logic.
    In addition, this [EASA] AD requires, prior to or concurrent 
with modification of an aeroplane with the activation of the SRIW, 
upgrades of the FAC and FWC, to introduce the SRIW logic and SRIW 
aural capability, respectively. After modification, this [EASA] AD 
prohibits installation of certain Part Number (P/N) FWC and FAC.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0251.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-22-1480, dated July 9, 
2014. The service information describes procedures for modifying the 
pin programming to activate the SRIW logic.
    Airbus has also issued the following service bulletins. The service 
information describes procedures for replacing FWCs and FACs.
     Airbus Service Bulletin A320-22-1375, dated January 15, 
2014.
     Airbus Service Bulletin A320-22-1427, Revision 04, dated 
February 11, 2014.
     Airbus Service Bulletin A320-22-1447, Revision 01, dated 
September 18, 2014.
     Airbus Service Bulletin A320-22-1461, Revision 04, dated 
September 15, 2014.
     Airbus Service Bulletin A320-31-1414, Revision 03, dated 
September 15, 2014.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement was a new process 
for annotating which procedures and tests in the service information 
are required for compliance with an AD. Differentiating these 
procedures and tests from other tasks in the service information is 
expected to improve an owner's/operator's understanding of crucial AD 
requirements and help provide consistent judgment in AD compliance. The 
actions specified in the service information identified previously 
include procedures and tests that are identified as RC (required for 
compliance) because these procedures have a direct effect on detecting, 
preventing, resolving, or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests identified as RC 
must be done to comply with the proposed AD. However, procedures and 
tests that are not identified as RC are recommended. Those procedures 
and tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an alternative method 
of compliance (AMOC), provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 953 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 work-hours per product 
to

[[Page 11962]]

comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $243,015, or $255 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 6 work-hours (3 work-hours for an FWC and 3 work-hours for 
an FAC), for a cost of up to $510 per product. We have received no 
definitive data that would enable us to provide part cost estimates for 
the on-condition actions specified in this proposed AD. We have no way 
of determining the number of aircraft that might need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect 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.
    For the reasons discussed above, I certify 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-
200-AD.

(a) Comments Due Date

    We must receive comments by April 20, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) through (c)(4) of this AD, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 22, Auto flight; 
31, Instruments.

(e) Reason

    This AD was prompted by a determination that, in specific flight 
conditions, the allowable load limits on the vertical tail plane 
could be reached and possibly exceeded. Exceeding allowable load 
could result in detachment of the vertical tail plane. We are 
issuing this AD to prevent detachment of the vertical tail plane and 
consequent loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Pin Programming Modification

    Within 48 months after the effective date of this AD, modify the 
pin programming to activate the stop rudder input warning (SRIW) 
logic, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-22-1480, dated July 9, 2014.

(h) Inspection To Determine Part Numbers (P/Ns), Flight Warning 
Computer (FWC) and Flight Augmentation Computer (FAC) Replacement

    Prior to or concurrently with, the actions required by paragraph 
(g) of this AD: Inspect the part numbers of the FWC and the FAC 
installed on the airplane. If any FWC or FAC having a part number 
identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, 
is installed on an airplane, prior to or concurrently with, the 
actions required by paragraph (g) of this AD, replace all affected 
FWCs and FACs with a unit having a part number identified in 
paragraph (h)(3) of this AD, in accordance with the Accomplishment 
Instructions of the applicable Airbus service bulletins specified in 
paragraph (i) of this AD.
    (1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD 
identify FWCs having part numbers that are non-compatible with the 
SRIW activation required by paragraph (g) of this AD.
    (i) 350E017238484 (H1D1).
    (ii) 350E053020303 (H2E3).
    (iii) 350E016187171 (C5).
    (iv) 350E053020404 (H2E4).
    (v) 350E017248685 (H1D2).
    (vi) 350E053020606 (H2F2).
    (vii) 350E017251414 (H1E1).
    (viii) 350E053020707 (H2F3).
    (ix) 350E017271616 (H1E2).
    (x) 350E053021010 (H2F3P).
    (xi) 350E018291818 (H1E3CJ).
    (xii) 350E053020808 (H2F4).
    (xiii) 350E018301919 (H1E3P).
    (xiv) 350E053020909 (H2-F5).
    (xv) 350E018312020 (H1E3Q).
    (xvi) 350E053021111 (H2-F6).
    (xvii) 350E053020202 (H2E2).
    (2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD 
identify FACs having part numbers that are non-compatible with the 
SRIW activation required by paragraph (g) of this AD.
    (i) B397AAM0202.
    (ii) B397BAM0101.
    (iii) B397BAM0512.
    (iv) B397AAM0301.
    (v) B397BAM0202.
    (vi) B397BAM0513.
    (vii) B397AAM0302.
    (viii) B397BAM0203.
    (ix) B397BAM0514.
    (x) B397AAM0303.
    (xi) B397BAM0305.
    (xii) B397BAM0515.
    (xiii) B397AAM0404.
    (xiv) B397BAM0406.
    (xv) B397BAM0616.
    (xvi) B397AAM0405.
    (xvii) B397BAM0407.
    (xviii) B397BAM0617.
    (xix) B397AAM0506.
    (xx) B397BAM0507.
    (xxi) B397BAM0618.
    (xxii) B397AAM0507.
    (xxiii) B397BAM0508.
    (xxiv) B397BAM0619.
    (xxv) B397AAM0508.
    (xxvi) B397BAM0509.
    (xxvii) B397BAM0620.
    (xxviii) B397AAM0509.
    (xxix) B397BAM0510.
    (xxx) B397CAM0101.

[[Page 11963]]

    (xxxi) B397AAM0510.
    (xxxii) B397BAM0511.
    (xxxiii) B397CAM0102.
    (xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00.
    (3) Paragraphs (h)(3)(i) through (h)(3)(iv) of this AD identify 
the FWCs and FACs having the part numbers that are compatible with 
SRIW activation required by paragraph (g) of this AD.
    (i) For airplane configurations with no sharklet, an FAC having 
P/N B397BAM0621 (621 hard B).
    (ii) For airplanes configured with sharklet A320 and A319, an 
FAC having P/N B397BAM0622 (622 hard B).
    (iii) For airplanes configured with sharklet A321, an FAC having 
P/N B397BAM0623 (623 hard B).
    (iv) For all airplane configurations, an FAC having soft P/N 
G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C) and FWC 
having P/N 350E053021212 (H2-F7).

(i) Service Bulletins for Actions Required by Paragraph (h) of This AD

    Do the actions required by paragraph (h) of this AD in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service bulletin specified in paragraphs (i)(1) through 
(i)(5) of this AD.
    (1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014 
(FAC 621 Hard B).
    (2) Airbus Service Bulletin A320-22-1427, Revision 04, dated 
February 11, 2014 (FAC 622 Hard B).
    (3) Airbus Service Bulletin A320-22-1447, Revision 01, dated 
September 18, 2014 (FAC A02 Hard C).
    (4) Airbus Service Bulletin A320-22-1461, Revision 04, dated 
September 15, 2014 (FAC 623 Hard B).
    (5) Airbus Service Bulletin A320-31-1414, Revision 03, dated 
September 15, 2014 (FWC H-F7).

(j) Exclusion From Actions Required by Paragraphs (g) and (h) of This 
AD

    An airplane on which Airbus Modification 154473 has been 
embodied in production is excluded from the requirements of 
paragraphs (g) and (h) of this AD, provided that, within 30 days 
after the effective date of this AD, an inspection of the part 
numbers of the FWC and the FAC installed on the airplane is done to 
determine that no FWC having a part number listed in paragraph 
(h)(1) of this AD, and no FAC having a part number part number 
listed in listed in paragraph (h)(2) of this AD, has been installed 
on that airplane since date of manufacture. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part numbers of the FWC and FAC can be conclusively determined from 
that review. If any FWC or FAC having a part number identified in 
paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed 
on a post-modification 154473 airplane: Within 30 days after the 
effective date of this AD, do the replacement required by paragraph 
(h) of this AD.

(k) Parts Installation Prohibitions

    After modification of an airplane as required by paragraphs (g), 
(h), and (j) of this AD: Do not install on that airplane any FWC 
having a part number listed in paragraph (h)(1) of this AD or any 
FAC having a part number listed in paragraph (h)(2) of this AD.

(l) Later Approved Parts

    Installation of a version (part number) of the FWC or FAC 
approved after the effective date of this AD is an approved method 
of compliance with the requirements of paragraph (h) or (j) of this 
AD, provided the requirements specified in paragraphs (l)(1) and 
(l)(2) of this AD are met.
    (1) The version (part number) must be approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA).
    (2) The installation must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using the Airbus service information identified in 
paragraphs (m)(1) through (m)(12) of this AD. This service 
information is not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A320-22-1427, dated January 25, 
2013.
    (2) Airbus Service Bulletin A320-22-1427, Revision 01, dated 
July 30, 2013.
    (3) Airbus Service Bulletin A320-22-1427, Revision 02, dated 
October 14, 2013.
    (4) Airbus Service Bulletin A320-22-1427, Revision 03, dated 
November 8, 2013.
    (5) Airbus Service Bulletin A320-22-1447, dated October 18, 
2013.
    (6) Airbus Service Bulletin A320-22-1461, dated October 31, 
2013.
    (7) Airbus Service Bulletin A320-22-1461, Revision 01, dated 
February 25, 2014.
    (8) Airbus Service Bulletin A320-22-1461, Revision 02, dated 
April 30, 2014.
    (9) Airbus Service Bulletin A320-22-1461, Revision 03, dated 
July 17, 2014.
    (10) Airbus Service Bulletin A320-31-1414, dated December 19, 
2012.
    (11) Airbus Service Bulletin A320-31-1414, Revision 01, dated 
March 21, 2013.
    (12) Airbus Service Bulletin A320-31-1414, Revision 02, dated 
July 30, 2013.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Required for Compliance (RC): If the service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures and tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.
    (3) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0217, dated September 26, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-0251.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.

    Issued in Renton, Washington, on February 19, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-04504 Filed 3-4-15; 8:45 am]
 BILLING CODE 4910-13-P

11960 Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules Conclusion extended configurations) in the DEPARTMENT OF TRANSPORTATION This action affects only certain novel following airspeed ranges: or unusual design features on two Federal Aviation Administration i. From 1.13 VSR1 to VMO/MMO. model series of airplanes. It is not a rule ii. From VMO/MMO to VFC/MFC, unless of general applicability. 14 CFR Part 39 the divergence is— [Docket No. FAA–2015–0251; Directorate List of Subjects in 14 CFR Part 25 (1) Gradual; Identifier 2014–NM–200–AD] Aircraft, Aviation safety, Reporting (2) Easily recognizable by the pilot; RIN 2120–AA64 and recordkeeping requirements. and The authority citation for these (3) Easily controllable by the pilot. Airworthiness Directives; Airbus special conditions is as follows: Airplanes (e) In straight, steady sideslips over Authority: 49 U.S.C. 106(g), 40113, 44701, the range of sideslip angles appropriate AGENCY: Federal Aviation 44702, 44704. to the operation of the airplane, but not Administration (FAA), DOT. The Proposed Special Conditions less than those obtained with one half ACTION: Notice of proposed rulemaking ■ Accordingly, the Federal Aviation of the available rudder control (NPRM). Administration proposes the following movement (but not exceeding a rudder control force of 180 pounds), rudder SUMMARY: We propose to adopt a new special conditions as part of the type airworthiness directive (AD) for all certification basis for Bombardier control movements and forces must be Airbus Model A318, A319, A320, and Aerospace BD–500–1A10 and BD–500– substantially proportional to the angle A321 series airplanes. This proposed 1A11 series airplanes. of sideslip in a stable sense; and the AD was prompted by a determination 1. Electronic Flight Control System: factor of proportionality must lie that, in specific flight conditions, the Lateral-Directional and Longitudinal between limits found necessary for safe allowable load limits on the vertical tail Stability and Low-Energy Awareness. In operation. This requirement must be plane could be reached and possibly lieu of the requirements of §§ 25.171, met for the configurations and speeds exceeded. Exceeding allowable load 25.173, 25.175, and 25.177: specified in paragraph (c) of this could result in detachment of the (a) The airplane must be shown to section. vertical tail plane. This proposed AD have suitable static lateral, directional, (f) For sideslip angles greater than would require modification of the pin and longitudinal stability in any those prescribed by paragraph (e) of this programming flight warning computer condition normally encountered in section, up to the angle at which full (FWC) to activate the stop rudder input service, including the effects of rudder control is used or a rudder warning (SRIW) logic; and an inspection atmospheric disturbance. The showing control force of 180 pounds is obtained, to determine the part numbers of the of suitable static lateral, directional, and the rudder control forces may not FWC and the flight augmentation longitudinal stability must be based on reverse, and increased rudder deflection computer (FAC), and replacement of the the airplane handling qualities, must be needed for increased angles of FWC and FAC if necessary. We are including pilot workload and pilot sideslip. Compliance with this proposing this AD to prevent compensation, for specific test requirement must be shown using detachment of the vertical tail plane and procedures during the flight test consequent loss of control of the evaluations. straight, steady sideslips, unless full (b) The airplane must provide airplane. lateral control input is achieved before adequate awareness to the pilot of a low reaching either full rudder control input DATES: We must receive comments on energy (low speed/low thrust/low or a rudder control force of 180 pounds; this proposed AD by April 20, 2015. height) state when fitted with flight a straight, steady sideslip need not be ADDRESSES: You may send comments, control laws presenting neutral maintained after achieving full lateral using the procedures found in 14 CFR longitudinal stability significantly control input. This requirement must be 11.43 and 11.45, by any of the following below the normal operating speeds. met at all approved landing gear and methods: ‘‘Adequate awareness’’ means warning wing-flap positions for the range of • Federal eRulemaking Portal: Go to information must be provided to alert operating speeds and power conditions http://www.regulations.gov. Follow the the crew of unsafe operating conditions appropriate to each landing gear and instructions for submitting comments. and to enable them to take appropriate • Fax: 202–493–2251. wing-flap position with all engines corrective action. • Mail: U.S. Department of (c) The static directional stability (as operating. Transportation, Docket Operations, M– shown by the tendency to recover from Issued in Renton, Washington, on February 30, West Building Ground Floor, Room a skid with the rudder free) must be 24, 2015. W12–140, 1200 New Jersey Avenue SE., positive for any landing gear and flap Jeffrey E. Duven, Washington, DC 20590. position and symmetrical power Manager, Transport Airplane Directorate, • Hand Delivery: U.S. Department of condition, at speeds from 1.13 VSR1, up Aircraft Certification Service. Transportation, Docket Operations, M– to VFE, VLE, or VFC/MFC (as appropriate). [FR Doc. 2015–05048 Filed 3–4–15; 8:45 am] 30, West Building Ground Floor, Room (d) The static lateral stability (as W12–140, 1200 New Jersey Avenue SE., BILLING CODE 4910–13–P shown by the tendency to raise the low Washington, DC, between 9 a.m. and mstockstill on DSK4VPTVN1PROD with PROPOSALS wing in a sideslip with the aileron 5 p.m., Monday through Friday, except controls free), for any landing-gear and Federal holidays. wing-flap position and symmetric- For service information identified in power condition, may not be negative at this proposed AD, contact Airbus, any airspeed (except that speeds higher Airworthiness Office—EIAS, 1 Rond than VFE need not be considered for Point Maurice Bellonte, 31707 Blagnac wing-flaps-extended configurations nor Cedex, France; telephone +33 5 61 93 36 speeds higher than VLE for landing-gear- 96; fax +33 5 61 93 44 51; email VerDate Sep<11>2014 19:43 Mar 04, 2015 Jkt 235001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\05MRP1.SGM 05MRP1

Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 11961 account.airworth-eas@airbus.com; Model A321 series airplanes. The MCAI FAA’s Determination and Requirements Internet http://www.airbus.com. You states: of This Proposed AD may view this referenced service During design reviews that were conducted This product has been approved by information at the FAA, Transport following safety recommendations related to the aviation authority of another Airplane Directorate, 1601 Lind Avenue in-service incidents and one accident on country, and is approved for operation SW., Renton, WA. For information on another aircraft type, it has been determined in the United States. Pursuant to our the availability of this material at the that, in specific flight conditions, the bilateral agreement with the State of FAA, call 425–227–1221. allowable load limits on the vertical tail plane could be reached and possibly Design Authority, we have been notified Examining the AD Docket exceeded. of the unsafe condition described in the This condition, if not corrected, could lead, MCAI and service information You may examine the AD docket on in the worst case, to detachment of the referenced above. We are proposing this the Internet at http:// vertical tail plane in flight and consequent AD because we evaluated all pertinent www.regulations.gov by searching for loss of the aeroplane. information and determined an unsafe and locating Docket No. FAA–2015– To prevent such a possibility, Airbus has condition exists and is likely to exist or 0251; or in person at the Docket developed modifications within the flight develop on other products of these same Management Facility between 9 a.m. augmentation computer (FAC) to reduce the type designs. and 5 p.m., Monday through Friday, vertical tail plane stress and to activate a except Federal holidays. The AD docket conditional aural warning within the flight Explanation of ‘‘RC’’ Procedures and contains this proposed AD, the warning computer (FWC) to further protect Tests in Service Information regulatory evaluation, any comments against pilot induced rudder doublets. For the reasons described above, this The FAA worked in conjunction with received, and other information. The industry, under the Airworthiness street address for the Docket Operations [EASA] AD requires installation and activation of the stop rudder input warning Directives Implementation Aviation office (telephone 800–647–5527) is in Rulemaking Committee (AD ARC), to (SRIW) logic. the ADDRESSES section. Comments will In addition, this [EASA] AD requires, prior enhance the AD system. One be available in the AD docket shortly to or concurrent with modification of an enhancement was a new process for after receipt. aeroplane with the activation of the SRIW, annotating which procedures and tests FOR FURTHER INFORMATION CONTACT: upgrades of the FAC and FWC, to introduce in the service information are required Sanjay Ralhan, Aerospace Engineer, the SRIW logic and SRIW aural capability, for compliance with an AD. International Branch, ANM–116, respectively. After modification, this [EASA] Differentiating these procedures and Transport Airplane Directorate, FAA, AD prohibits installation of certain Part Number (P/N) FWC and FAC. tests from other tasks in the service 1601 Lind Avenue SW., Renton, WA information is expected to improve an 98057–3356; telephone 425–227–1405; You may examine the MCAI in the AD owner’s/operator’s understanding of fax 425–227–1149. docket on the Internet at http:// crucial AD requirements and help SUPPLEMENTARY INFORMATION: www.regulations.gov by searching for provide consistent judgment in AD and locating Docket No. FAA–2015– compliance. The actions specified in the Comments Invited 0251. service information identified We invite you to send any written previously include procedures and tests relevant data, views, or arguments about Related Service Information Under 1 that are identified as RC (required for this proposed AD. Send your comments CFR Part 51 compliance) because these procedures to an address listed under the Airbus has issued Service Bulletin have a direct effect on detecting, ADDRESSES section. Include ‘‘Docket No. A320–22–1480, dated July 9, 2014. The preventing, resolving, or eliminating an FAA–2015–0251; Directorate Identifier service information describes identified unsafe condition. 2014–NM–200–AD’’ at the beginning of procedures for modifying the pin As specified in a NOTE under the your comments. We specifically invite programming to activate the SRIW logic. Accomplishment Instructions of the comments on the overall regulatory, Airbus has also issued the following specified service information, economic, environmental, and energy service bulletins. The service procedures and tests identified as RC aspects of this proposed AD. We will information describes procedures for must be done to comply with the consider all comments received by the replacing FWCs and FACs. proposed AD. However, procedures and closing date and may amend this • Airbus Service Bulletin A320–22– tests that are not identified as RC are proposed AD based on those comments. 1375, dated January 15, 2014. recommended. Those procedures and We will post all comments we tests that are not identified as RC may • Airbus Service Bulletin A320–22– receive, without change, to http:// be deviated from using accepted 1427, Revision 04, dated February 11, www.regulations.gov, including any methods in accordance with the 2014. personal information you provide. We operator’s maintenance or inspection will also post a report summarizing each • Airbus Service Bulletin A320–22– program without obtaining approval of substantive verbal contact we receive 1447, Revision 01, dated September 18, an alternative method of compliance about this proposed AD. 2014. (AMOC), provided the procedures and • Airbus Service Bulletin A320–22– tests identified as RC can be done and Discussion 1461, Revision 04, dated September 15, the airplane can be put back in a The European Aviation Safety Agency 2014. serviceable condition. Any substitutions (EASA), which is the Technical Agent • Airbus Service Bulletin A320–31– mstockstill on DSK4VPTVN1PROD with PROPOSALS or changes to procedures or tests for the Member States of the European 1414, Revision 03, dated September 15, identified as RC will require approval of Community, has issued EASA 2014. an AMOC. Airworthiness Directive 2014–0217, The actions described in this service dated September 26, 2014 (referred to information are intended to correct the Costs of Compliance after this as the Mandatory Continuing unsafe condition identified in the We estimate that this proposed AD Airworthiness Information, or ‘‘the MCAI. This service information is affects 953 airplanes of U.S. registry. MCAI’’), to correct an unsafe condition reasonably available; see ADDRESSES for We also estimate that it would take for all Model A318, A319, A320, and ways to access this service information. about 3 work-hours per product to VerDate Sep<11>2014 19:43 Mar 04, 2015 Jkt 235001 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 E:\FR\FM\05MRP1.SGM 05MRP1

11962 Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules comply with the basic requirements of List of Subjects in 14 CFR Part 39 (h) Inspection To Determine Part Numbers this proposed AD. The average labor (P/Ns), Flight Warning Computer (FWC) and Air transportation, Aircraft, Aviation Flight Augmentation Computer (FAC) rate is $85 per work-hour. Based on safety, Incorporation by reference, Replacement these figures, we estimate the cost of Safety. this proposed AD on U.S. operators to Prior to or concurrently with, the actions be $243,015, or $255 per product. The Proposed Amendment required by paragraph (g) of this AD: Inspect the part numbers of the FWC and the FAC In addition, we estimate that any Accordingly, under the authority installed on the airplane. If any FWC or FAC necessary follow-on actions would take delegated to me by the Administrator, having a part number identified in paragraph about 6 work-hours (3 work-hours for an the FAA proposes to amend 14 CFR part (h)(1) or (h)(2) of this AD, as applicable, is FWC and 3 work-hours for an FAC), for 39 as follows: installed on an airplane, prior to or a cost of up to $510 per product. We concurrently with, the actions required by have received no definitive data that PART 39—AIRWORTHINESS paragraph (g) of this AD, replace all affected would enable us to provide part cost DIRECTIVES FWCs and FACs with a unit having a part estimates for the on-condition actions number identified in paragraph (h)(3) of this specified in this proposed AD. We have ■ 1. The authority citation for part 39 AD, in accordance with the Accomplishment continues to read as follows: Instructions of the applicable Airbus service no way of determining the number of bulletins specified in paragraph (i) of this aircraft that might need these actions. Authority: 49 U.S.C. 106(g), 40113, 44701. AD. (1) Paragraphs (h)(1)(i) through (h)(1)(xvii) Authority for This Rulemaking § 39.13 [Amended] of this AD identify FWCs having part Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding numbers that are non-compatible with the specifies the FAA’s authority to issue the following new airworthiness SRIW activation required by paragraph (g) of rules on aviation safety. Subtitle I, directive (AD): this AD. Airbus: Docket No. FAA–2015–0251; (i) 350E017238484 (H1D1). section 106, describes the authority of Directorate Identifier 2014–NM–200–AD. (ii) 350E053020303 (H2E3). the FAA Administrator. ‘‘Subtitle VII: (iii) 350E016187171 (C5). Aviation Programs,’’ describes in more (a) Comments Due Date (iv) 350E053020404 (H2E4). detail the scope of the Agency’s We must receive comments by April 20, (v) 350E017248685 (H1D2). authority. 2015. (vi) 350E053020606 (H2F2). We are issuing this rulemaking under (vii) 350E017251414 (H1E1). (b) Affected ADs (viii) 350E053020707 (H2F3). the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: None. (ix) 350E017271616 (H1E2). (x) 350E053021010 (H2F3P). General requirements.’’ Under that (c) Applicability (xi) 350E018291818 (H1E3CJ). section, Congress charges the FAA with This AD applies to the airplanes, (xii) 350E053020808 (H2F4). promoting safe flight of civil aircraft in certificated in any category, identified in (xiii) 350E018301919 (H1E3P). air commerce by prescribing regulations paragraphs (c)(1) through (c)(4) of this AD, all (xiv) 350E053020909 (H2–F5). for practices, methods, and procedures manufacturer serial numbers. (xv) 350E018312020 (H1E3Q). the Administrator finds necessary for (1) Airbus Model A318–111, –112, –121, (xvi) 350E053021111 (H2–F6). safety in air commerce. This regulation and –122 airplanes. (xvii) 350E053020202 (H2E2). (2) Airbus Model A319–111, –112, –113, (2) Paragraphs (h)(2)(i) through is within the scope of that authority –114, –115, –131, –132, and –133 airplanes. (h)(2)(xxxiv) of this AD identify FACs having because it addresses an unsafe condition (3) Airbus Model A320–211, –212, –214, part numbers that are non-compatible with that is likely to exist or develop on –231, –232, and –233 airplanes. the SRIW activation required by paragraph products identified in this rulemaking (4) Airbus Model A321–111, –112, –131, (g) of this AD. action. –211, –212, –213, –231, and –232 airplanes. (i) B397AAM0202. (d) Subject (ii) B397BAM0101. Regulatory Findings (iii) B397BAM0512. Air Transport Association (ATA) of (iv) B397AAM0301. We determined that this proposed AD America Code 22, Auto flight; 31, would not have federalism implications (v) B397BAM0202. Instruments. (vi) B397BAM0513. under Executive Order 13132. This (e) Reason (vii) B397AAM0302. proposed AD would not have a (viii) B397BAM0203. substantial direct effect on the States, on This AD was prompted by a determination (ix) B397BAM0514. the relationship between the national that, in specific flight conditions, the (x) B397AAM0303. Government and the States, or on the allowable load limits on the vertical tail (xi) B397BAM0305. plane could be reached and possibly distribution of power and exceeded. Exceeding allowable load could (xii) B397BAM0515. responsibilities among the various (xiii) B397AAM0404. result in detachment of the vertical tail plane. levels of government. We are issuing this AD to prevent (xiv) B397BAM0406. For the reasons discussed above, I detachment of the vertical tail plane and (xv) B397BAM0616. consequent loss of control of the airplane. (xvi) B397AAM0405. certify this proposed regulation: (xvii) B397BAM0407. 1. Is not a ‘‘significant regulatory (f) Compliance (xviii) B397BAM0617. action’’ under Executive Order 12866; Comply with this AD within the (xix) B397AAM0506. 2. Is not a ‘‘significant rule’’ under the compliance times specified, unless already (xx) B397BAM0507. DOT Regulatory Policies and Procedures (xxi) B397BAM0618. mstockstill on DSK4VPTVN1PROD with PROPOSALS done. (44 FR 11034, February 26, 1979); (xxii) B397AAM0507. (g) Pin Programming Modification (xxiii) B397BAM0508. 3. Will not affect intrastate aviation in Alaska; and Within 48 months after the effective date (xxiv) B397BAM0619. of this AD, modify the pin programming to (xxv) B397AAM0508. 4. Will not have a significant activate the stop rudder input warning (xxvi) B397BAM0509. economic impact, positive or negative, (SRIW) logic, in accordance with the (xxvii) B397BAM0620. on a substantial number of small entities Accomplishment Instructions of Airbus (xxviii) B397AAM0509. under the criteria of the Regulatory Service Bulletin A320–22–1480, dated July 9, (xxix) B397BAM0510. Flexibility Act. 2014. (xxx) B397CAM0101. VerDate Sep<11>2014 19:43 Mar 04, 2015 Jkt 235001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\05MRP1.SGM 05MRP1

Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 11963 (xxxi) B397AAM0510. AD: Do not install on that airplane any FWC telephone 425–227–1405; fax 425–227–1149. (xxxii) B397BAM0511. having a part number listed in paragraph Information may be emailed to: 9-ANM-116- (xxxiii) B397CAM0102. (h)(1) of this AD or any FAC having a part AMOC-REQUESTS@faa.gov. Before using (xxxiv) Soft P/N G2856AAA01 installed on number listed in paragraph (h)(2) of this AD. any approved AMOC, notify your appropriate hard P/N C13206AA00. principal inspector, or lacking a principal (l) Later Approved Parts (3) Paragraphs (h)(3)(i) through (h)(3)(iv) of Installation of a version (part number) of inspector, the manager of the local flight this AD identify the FWCs and FACs having the part numbers that are compatible with the FWC or FAC approved after the effective standards district office/certificate holding SRIW activation required by paragraph (g) of date of this AD is an approved method of district office. The AMOC approval letter this AD. compliance with the requirements of must specifically reference this AD. (i) For airplane configurations with no paragraph (h) or (j) of this AD, provided the (2) Required for Compliance (RC): If the sharklet, an FAC having P/N B397BAM0621 requirements specified in paragraphs (l)(1) service information contains procedures or (621 hard B). and (l)(2) of this AD are met. tests that are identified as RC, those (ii) For airplanes configured with sharklet (1) The version (part number) must be procedures and tests must be done to comply A320 and A319, an FAC having P/N approved by the Manager, International with this AD; any procedures and tests that B397BAM0622 (622 hard B). Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation are not identified as RC are recommended. (iii) For airplanes configured with sharklet A321, an FAC having P/N B397BAM0623 Safety Agency (EASA); or Airbus’s EASA Those procedures and tests that are not (623 hard B). Design Organization Approval (DOA). identified as RC may be deviated from using (iv) For all airplane configurations, an FAC (2) The installation must be accomplished accepted methods in accordance with the having soft P/N G2856AAA02 installed on using a method approved by the Manager, operator’s maintenance or inspection hard P/N C13206AA00 (CAA02 hard C) and International Branch, ANM–116, Transport program without obtaining approval of an FWC having P/N 350E053021212 (H2–F7). Airplane Directorate, FAA; or EASA; or AMOC, provided the procedures and tests Airbus’s EASA DOA. identified as RC can be done and the airplane (i) Service Bulletins for Actions Required by Paragraph (h) of This AD (m) Credit for Previous Actions can be put back in a serviceable condition. This paragraph provides credit for actions Any substitutions or changes to procedures Do the actions required by paragraph (h) of this AD in accordance with the required by paragraph (h) of this AD, if those or tests identified as RC require approval of Accomplishment Instructions of the actions were performed before the effective an AMOC. applicable Airbus service bulletin specified date of this AD using the Airbus service (3) Contacting the Manufacturer: For any in paragraphs (i)(1) through (i)(5) of this AD. information identified in paragraphs (m)(1) requirement in this AD to obtain corrective (1) Airbus Service Bulletin A320–22–1375, through (m)(12) of this AD. This service actions from a manufacturer, the action must dated January 15, 2014 (FAC 621 Hard B). information is not incorporated by reference be accomplished using a method approved (2) Airbus Service Bulletin A320–22–1427, in this AD. by the Manager, International Branch, ANM– Revision 04, dated February 11, 2014 (FAC (1) Airbus Service Bulletin A320–22–1427, 116, Transport Airplane Directorate, FAA; or 622 Hard B). dated January 25, 2013. the EASA; or Airbus’s EASA DOA. If (3) Airbus Service Bulletin A320–22–1447, (2) Airbus Service Bulletin A320–22–1427, Revision 01, dated July 30, 2013. approved by the DOA, the approval must Revision 01, dated September 18, 2014 (FAC A02 Hard C). (3) Airbus Service Bulletin A320–22–1427, include the DOA-authorized signature. (4) Airbus Service Bulletin A320–22–1461, Revision 02, dated October 14, 2013. (o) Related Information Revision 04, dated September 15, 2014 (FAC (4) Airbus Service Bulletin A320–22–1427, 623 Hard B). Revision 03, dated November 8, 2013. (1) Refer to Mandatory Continuing (5) Airbus Service Bulletin A320–31–1414, (5) Airbus Service Bulletin A320–22–1447, Airworthiness Information (MCAI) EASA Revision 03, dated September 15, 2014 (FWC dated October 18, 2013. Airworthiness Directive 2014–0217, dated H–F7). (6) Airbus Service Bulletin A320–22–1461, September 26, 2014, for related information. dated October 31, 2013. This MCAI may be found in the AD docket (j) Exclusion From Actions Required by (7) Airbus Service Bulletin A320–22–1461, Paragraphs (g) and (h) of This AD on the Internet at http://www.regulations.gov Revision 01, dated February 25, 2014. by searching for and locating Docket No. An airplane on which Airbus Modification (8) Airbus Service Bulletin A320–22–1461, FAA–2015–0251. 154473 has been embodied in production is Revision 02, dated April 30, 2014. excluded from the requirements of (9) Airbus Service Bulletin A320–22–1461, (2) For service information identified in paragraphs (g) and (h) of this AD, provided Revision 03, dated July 17, 2014. this AD, contact Airbus, Airworthiness that, within 30 days after the effective date (10) Airbus Service Bulletin A320–31– Office—EIAS, 1 Rond Point Maurice of this AD, an inspection of the part numbers 1414, dated December 19, 2012. Bellonte, 31707 Blagnac Cedex, France; of the FWC and the FAC installed on the (11) Airbus Service Bulletin A320–31– telephone +33 5 61 93 36 96; fax +33 5 61 airplane is done to determine that no FWC 1414, Revision 01, dated March 21, 2013. 93 44 51; email account.airworth-eas@ having a part number listed in paragraph (12) Airbus Service Bulletin A320–31– airbus.com; Internet http://www.airbus.com. (h)(1) of this AD, and no FAC having a part 1414, Revision 02, dated July 30, 2013. You may view this service information at the number part number listed in listed in FAA, Transport Airplane Directorate, 1601 (n) Other FAA AD Provisions paragraph (h)(2) of this AD, has been The following provisions also apply to this Lind Avenue SW., Renton, WA. For installed on that airplane since date of manufacture. A review of airplane AD: information on the availability of this maintenance records is acceptable in lieu of (1) Alternative Methods of Compliance material at the FAA, call 425–227–1221. this inspection if the part numbers of the (AMOCs): The Manager, International Issued in Renton, Washington, on February FWC and FAC can be conclusively Branch, ANM–116, Transport Airplane 19, 2015. determined from that review. If any FWC or Directorate, FAA, has the authority to FAC having a part number identified in approve AMOCs for this AD, if requested John P. Piccola, Jr., using the procedures found in 14 CFR 39.19. mstockstill on DSK4VPTVN1PROD with PROPOSALS paragraph (h)(1) or (h)(2) of this AD, as Acting Manager, Transport Airplane applicable, is installed on a post- In accordance with 14 CFR 39.19, send your Directorate, Aircraft Certification Service. modification 154473 airplane: Within 30 request to your principal inspector or local [FR Doc. 2015–04504 Filed 3–4–15; 8:45 am] days after the effective date of this AD, do the Flight Standards District Office, as replacement required by paragraph (h) of this appropriate. If sending information directly BILLING CODE 4910–13–P AD. to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, (k) Parts Installation Prohibitions International Branch, ANM–116, Transport After modification of an airplane as Airplane Directorate, FAA, 1601 Lind required by paragraphs (g), (h), and (j) of this Avenue SW., Renton, WA 98057–3356; VerDate Sep<11>2014 19:43 Mar 04, 2015 Jkt 235001 PO 00000 Frm 00018 Fmt 4702 Sfmt 9990 E:\FR\FM\05MRP1.SGM 05MRP1


Document Created: 2015-12-18 12:09:08
Document Modified: 2015-12-18 12:09:08
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by April 20, 2015.
ContactSanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149.
FR Citation80 FR 11960 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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