Document ID: FAA-2011-0479-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 Airplanes; Equipped with Certain Cockpit Door Installations
Posted Date: 2011-10-12T04:00Z

[Federal Register Volume 76, Number 197 (Wednesday, October 12, 2011)]
[Rules and Regulations]
[Pages 63169-63172]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-25770]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0479; Directorate Identifier 2010-NM-154-AD; 
Amendment 39-16827; AD 2011-21-04]
RIN 2120-AA64

Airworthiness Directives; Bombardier Inc. Model DHC-8-102, -103, 
-106, -201, -202, -301, -311, and -315 Airplanes; Equipped With Certain 
Cockpit Door Installations

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to the products listed above. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected, 
could result in breakage and uncontrolled release of the cockpit 
door under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective November 16, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 16, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, as of July, 18, 2006 (71 FR 34006, June 13, 2006).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Andreas Rambalakos, Aerospace 
Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New 
York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, 
Westbury, New York 11590; telephone (516) 228-7345; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 8, 2011 (76 FR 
33173), and proposed to supersede AD 2006-12-16, Amendment 39-14642 (71 
FR 34006, June 13, 2006). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected, 
could result in breakage and uncontrolled release of the cockpit 
door under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * *, an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. 
Therefore, * * * this [Canadian] directive is issued to require 
rework of the cockpit door striker plate and replacement of the 
latch block for the affected aircraft serial numbers. * * *

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM (76 FR 33173, June 8, 2011).

Conclusion

    We reviewed the available data, including the comment received, and

[[Page 63170]]

determined that air safety and the public interest require adopting the 
AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 17 products of U.S. 
registry.
    The actions that are required by AD 2006-12-16 (71 FR 34006, June 
13, 2006) and retained in this AD take between 3 and 6 work-hours per 
product, at an average labor rate of $85 per work-hour. Required parts 
cost about $2,000 per product. Based on these figures, the estimated 
cost of the currently required actions is between $2,255 and $2,510 per 
product.
    We estimate that it will take about 3 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $2,000 per 
product. Where the service information lists required parts costs that 
are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $38,335, or $2,255 per product.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 33173, June 8, 2011), 
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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 removing Amendment 39-14642 (71 FR 
34006, June 13, 2006) and adding the following new AD:

2011-21-04 Bombardier Inc.: Amendment 39-16827. Docket No. FAA-2011-
0479; Directorate Identifier 2010-NM-154-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
16, 2011.

Affected ADs

    (b) This AD supersedes AD 2006-12-16, Amendment 39-14642 (71 FR 
34006, June 13, 2006).

Applicability

    (c) This AD applies to Bombardier Model DHC-8-102, -103, -106, -
201, -202, -301, -311, and -315 airplanes, certificated in any 
category; serial numbers (S/Ns) 003 through 557 inclusive; equipped 
with cockpit door installation part numbers (P/Ns) identified in 
table 1 of this AD.

         Table 1--Cockpit Door Installations Affected by This AD
------------------------------------------------------------------------
                  P/N                             Dash number(s)
------------------------------------------------------------------------
82510074...............................  All.
82510294...............................  All.
82510310...............................  -001.
8Z4597.................................  -001.
H85250010..............................  All.
82510700...............................  All.
82510704...............................  All except -502
                                         and -503.
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 52: Doors.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During structural testing of the cockpit door, it was observed 
that the door lower hinge block rotated which resulted in 
disengagement of the mating hinge pin and excessive door deflection. 
The lower hinge block rotated because it was attached to its support 
structure with only one attachment bolt, which prevented it from 
reacting to any moment force. This condition, if not corrected, 
could result in breakage and uncontrolled release of the cockpit 
door under certain decompression situations.
    After incorporation of Modsum 8Q900267 * * * an operator 
reported a failure to complete the cockpit door removal function 
test. This condition, if not corrected, could result in the 
inability to remove the cockpit door for emergency egress. * * *

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

[[Page 63171]]

Restatement of Requirements of AD 2006-12-16 Amendment 39-14642 (71 FR 
34006, June 13, 2006), With New Service Information

Modification

    (g) Within 24 months after July 18, 2006 (the effective date of 
AD 2006-12-16 Amendment 39-14642 (71 FR 34006, June 13, 2006)), 
modify the cockpit door from a single-point attachment to a two-
point attachment in accordance with the Accomplishment Instructions 
of the applicable service bulletin in table 2 of this AD. For 
airplane serial numbers 452, 464, 490, 506, and 508 through 557 
inclusive: After the effective date of this AD, use Bombardier 
Service Bulletin 8-52-58, Revision A, dated November 17, 2006.

   Table 2--Bombardier Service Bulletins for Modification Required by
                        Paragraph (g) of This AD
------------------------------------------------------------------------
 Use this Bombardier Service Bulletin--   For airplane serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated November 5,   003 through 451 inclusive, 453
 2004.                                    through 463 inclusive, 465
                                          through 489 inclusive, 491
                                          through 505 inclusive, and
                                          507.
8-52-58, dated May 12, 2004, or          452, 464, 490, 506, and 508
 Revision A, dated November 17, 2006.     through 557 inclusive.
------------------------------------------------------------------------

    Note 1:  Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, refers to Bombardier Series 100/300 Modification 
Summary (Modsum) 8Q100859 as an additional source of guidance for 
installing a hinge pin with a two-point attachment. Bombardier 
Service Bulletin 8-52-58, dated May 12, 2004, or Revision A, dated 
November 17, 2006, refers to Bombardier Series 100/300 Modsum 
8Q900267 as an additional source of guidance for reworking and 
installing the cockpit door, and reworking the lower hinge 
attachment to provide a downward-facing pin with a two-point 
attachment.

Prior/Concurrent Requirements

    (h) Prior to or concurrently with the modification in paragraph 
(g) of this AD, do the applicable actions specified in table 3 of 
this AD, in accordance with a method approved by either the Manager, 
New York Aircraft Certification (ACO), FAA; or Transport Canada 
Civil Aviation (TCCA) (or its delegated agent).

 Table 3--Bombardier Service Bulletins for Requirements of Paragraph (h)
                               of This AD
------------------------------------------------------------------------
  For airplanes affected by
Bombardier Service Bulletin--    That have these     Do these actions--
                                serial numbers--
------------------------------------------------------------------------
8-52-54, Revision A, dated    003 through 407       Rework the cockpit
 November 5, 2004.             inclusive, 409        door emergency
                               through 412           release.
                               inclusive, and 414
                               through 433
                               inclusive.
                                                    Install a new label
                                                     regarding alternate
                                                     release of the
                                                     door.
8-52-58, dated May 12, 2004,  452, 464, 490, 506,   Install the cockpit
 or Revision A, dated          and 508 through 557   door.
 November 17, 2006.            inclusive.
------------------------------------------------------------------------

    Note 2:  Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, refers to De Havilland Aircraft of Canada, 
Limited, Modification 8/2337 as an additional source of guidance for 
reworking the cockpit door emergency release; and Modification 8/
3339 as additional source of guidance for installing a new label 
regarding alternate release of the door; on airplanes having serial 
numbers 003 through 407 inclusive, 409 through 412 inclusive, and 
414 through 433 inclusive.

    Note 3:  Bombardier Service Bulletins 8-52-58, dated May 12, 
2004; and Revision A, dated November 17, 2006; refer to Bombardier 
Modsum 8Q200015, as an additional source of guidance for installing 
the cockpit door, on airplanes having serial numbers 452, 464, 490, 
506, and 508 through 557 inclusive.

Actions Done in Accordance With Previous Revision of Service Bulletin

    (i) Actions done before July 18, 2006, in accordance with 
Bombardier Service Bulletin 8-52-54, dated May 12, 2004, are 
acceptable for compliance with the corresponding requirements in 
paragraph (g) of this AD.

New Requirements of This AD

    (j) For airplanes having S/N 452, 464, 490, 506, and 508 through 
557 inclusive, and on which the requirements in paragraph (g) of 
this AD have been done as of the effective date of this AD: Within 
12 months after the effective date of this AD rework the cockpit 
door striker plate and replace the latch block, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-52-
61, dated October 20, 2006.
    (k) For airplanes having S/Ns 452, 464, 490, 506, and 508 
through 557 inclusive, and on which the requirements in paragraph 
(g) of this AD have not been done as of the effective date of this 
AD: Prior to or concurrently with doing the modification required in 
paragraph (g) of this AD, rework the cockpit door striker plate and 
replace the latch block, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 8-52-61, dated October 
20, 2006.

FAA AD Differences

    Note 4: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (l) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office, ANE-170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, 
New York 11590; telephone 516-228-7300; fax 516-794-5531. 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

Related Information

    (m) Refer to MCAI Canadian Airworthiness Directive CF-2005-34R1, 
dated August 15, 2007; Bombardier Service Bulletin 8-52-54, Revision 
A, dated November 5, 2004;

[[Page 63172]]

Bombardier Service Bulletin 8-52-58, Revision A, dated November 17, 
2006; and Bombardier Service Bulletin 8-52-61, dated October 20, 
2006; for related information.

Material Incorporated by Reference

    (n) You must use the following service information to do the 
applicable actions required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR 
Part 51 of the following service information on the date specified:
    (1) Bombardier Service Bulletin 8-52-58, Revision A, dated 
November 17, 2006, approved for IBR November 16, 2011;
    (2) Bombardier Service Bulletin 8-52-61, dated October 20, 2006, 
approved for IBR November 16, 2011;
    (3) Bombardier Service Bulletin 8-52-54, Revision A, dated 
November 5, 2004, approved for IBR July 18, 2006 (71 FR 34006, June 
13, 2006).
    (4) For service information identified in this AD, contact 
Bombardier Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; e-mail thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com.
    (5) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (6) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 23, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-25770 Filed 10-11-11; 8:45 am]
BILLING CODE 4910-13-P