### 59630 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations

Region

No. Area within region Office address

V .......... Alaska, Arizona, California, Guam, Hawaii, Idaho, Nevada, Oregon, Utah, Washington. 1230 W. Washington Street, Suite 301, Tempe, AZ 85281.

* * * * *

[FR Doc. 2014–22715 Filed 10–2–14; 8:45 am]

**BILLING CODE 7535–01–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1067; Directorate Identifier 2013–NM–164–AD; Amendment**  **39–17982; AD 2014–20–09]**

**RIN 2120–AA64**

**Airworthiness Directives; Bombardier, Inc. Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted by reports of missing clamps that are required to provide positive separation between the alternating current (AC) feeder cables and the hydraulic line of the landing gear alternate extension. This AD requires an inspection for missing clamps that are required to provide positive separation between the AC feeder cables and the hydraulic line of the landing gear alternate extension, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct chafing of the AC feeder cable. A chafed and arcing AC feeder cable could puncture the adjacent hydraulic line, which, in
combination with the use of the alternate extension system, could result in an in-flight fire.

**DATES :**  This AD becomes effective November 7, 2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 7, 2014.

**ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1067 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified inthis AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@ aero.bombardier.com; Internet http://
www.bombardier.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.

**FOR FURTHER INFORMATION CONTACT :**  Assata Dessaline, Aerospace Engineer, Avionics and Service Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7301; fax 516–794–5531.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model DHC–8–400 series airplanes. The NPRM published in the Federal Register on December 30, 2013 (78 FR 79338).

Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2013–16, dated June 14, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI

states:

During production checks, it was found that the appropriate clamps required to provide positive separation between the AC feeder cables and the hydraulic line of the landing gear alternate extension were omitted. The AC feeder cable could sag and be in direct contact with the swage fitting of the landing gear alternate extension hydraulic line, resulting in chafing of the AC feeder cable. The chafed and arcing AC feeder cable could puncture the adjacent hydraulic line. In combination with the use of the alternate extension system, this could result in an in-flight fire.

This [Canadian] AD mandates the [general visual] inspection [for missing clamps], and rectification [related investigative and corrective actions] as necessary, for proper clamp installation.

The related investigative action is a general visual inspection of the AC power feeder cables and the hydraulic line for damage due to chafing. The corrective actions include repair of chafed parts, and replacement of missing clamps. You may examine the
MCAI in the AD docket on the Internet

at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-1067-

0002.

Comment

We gave the public the opportunity to participate in developing this AD. We
have considered the comment received. The following presents the comment received on the NPRM (78 FR 79338, December 30, 2013) and the FAA’s response to the comment.

Request To Remove Certain Service
Information Procedures

Horizon Air requested that we change the language in paragraph (g) of the NPRM (78 FR 79338, December 30, 2013) from mandating the Accomplishment Instructions in Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013, to mandating only the section of Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013, that
corrects the unsafe condition. Horizon Air stated that the Accomplishment Instructions, Part A, ‘‘Job Set-up,’’ and Part C, ‘‘Close Out,’’ have nothing to do with correcting the unsafe condition. Horizon Air expressed that mandating operators to perform these sections adds an unnecessary regulatory requirement because operators must have the airplane in a specific condition, and keep it in that condition, while performing the corrective action. Horizon Air also stated that, if the FAA keeps the requirements of job setup and job close-out, it forces an operator to request an alternative method of compliance (AMOC) if it chooses to deviate from the work-steps. Horizon Air provided its cost estimate of obtaining an AMOC.

In this case, we agree with the commenter’s request to exclude the ‘‘Job Set-up’’ and ‘‘Close Out’’ sections of Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013. We have revised paragraph (g) of this AD to require accomplishment of paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013.


### 59631 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations

‘‘Contacting the Manufacturer’’ Paragraph in This AD

Since late 2006, we have included a standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD.

The MCAI or referenced service
information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved.

In the NPRM (78 FR 79338, December 30, 2013), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority design organization approval (DOA), as applicable, to refer to a DAH authorized to approve required repairs for the proposed AD.

No comments were provided to the NPRM (78 FR 79338, December 30, 2013) about these proposed changes. However, a comment was provided for another NPRM, Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013), in which the commenter stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment
of an AD mandated Airbus service
bulletin.’’

This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the
manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19.

To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed that paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the FAA, TCCA, or Bombardier’s TCCA Design Approval Organization (DAO). Where necessary throughout this AD, we also replaced any reference to approvals of corrective
actions with a reference to the Contacting the Manufacturer paragraph.

The Contacting the Manufacturer paragraph also clarifies that, if approved by the DAO, the approval must include the DAO-authorized signature. The DAO signature indicates that the data and
information contained in the documentare TCCA-approved, which is also FAAapproved. Messages and other information provided by the
manufacturer that do not contain the DAO-authorized signature approval are not TCCA-approved, unless TCCA directly approves the manufacturer’s message or other information.

This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is
also consistent with the
recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in
manufacturers’ service instructions that are ‘‘Required for Compliance’’ with
ADs. We continue to work with manufacturers to implement this
recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance.

Other commenters to the NPRM discussed previously, Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013), pointed out that in many cases the foreign manufacturer’s service bulletin and the foreign authority’s MCAI might have
been issued some time before the FAA AD. Therefore, the DOA might have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition,
before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the
manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit.

Based on these comments, weremoved the requirement that the DAHprovided repair specifically refer to this AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the
unsafe condition addressed in this AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘DAH with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (78 FR 79338, December 30, 2013) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 79338, December 30, 2013).

We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD.

Costs of Compliance

We estimate that this AD affects 78 airplanes of U.S. registry.

We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures,
we estimate the cost of this AD on U.S. operators to be $13,260, or $170 per product.


### 59632 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations

In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $11, for a cost of $181 per product. We have received no definitive data that would enable us to provide
cost estimates for the on-condition repair of the AC power feeder cables and hydraulic lines specified in this 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 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 that 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);

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.

Examining the AD Docket

You may examine the AD docket on
the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1067; 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 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.

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**

■ 1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

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

2014–20–09 Bombardier, Inc.: Amendment 39–17982. Docket No. FAA–2013–1067;
Directorate Identifier 2013–NM–164–AD.

(a) Effective Date

This AD becomes effective November 7,

2014.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes, certificated in any category, serial numbers 4001 through 4347 inclusive.

(d) Subject

Air Transport Association (ATA) of America Code 24, Electrical power.

(e) Reason

This AD was prompted by reports of missing clamps that are required to provide positive separation between the alternating current (AC) feeder cables and the hydraulic line of the landing gear alternate extension. We are issuing this AD to detect and correct chafing of the AC feeder cable. A chafed and arcing AC feeder cable could puncture the adjacent hydraulic line, which, in
combination with the use of the alternate extension system, could result in an in-flight
fire.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done. (g) Clamp Inspection, Related Investigative Actions, and Corrective Actions

Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs earlier: Do a general visual inspection for installation of clamps between the AC feeder cables and hydraulic line; and do all applicable related investigative and corrective actions; in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013. Do all applicable related investigative and corrective actions before further flight.

(h) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84–24–53, dated May 11, 2012.

(i) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), 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, NY 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) 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, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO,the approval must include the DAOauthorized signature.

(j) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–16, dated June 14, 2013, for related information. This MCAI may be found in the AD docket on the

Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-1067-0002.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD.

(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this


### 59633 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations

paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(i) Bombardier Service Bulletin 84–24–53, Revision A, dated May 16, 2013.

(ii) Reserved. (3) 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;
email thd.qseries@aero.bombardier.com;

Internet http://www.bombardier.com.

(4) 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.

(5) You may view this 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/cfr/ibrlocations.html.

Issued in Renton, Washington, on September 23, 2014.

Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–23429 Filed 10–2–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0283; Directorate Identifier 2012–NM–183–AD; Amendment**  **39–17980; AD 2014–20–07]**

**RIN 2120–AA64**

**Airworthiness Directives; the Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2010–03– 05 for all the Boeing Company Model 747–200C and –200F series airplanes. AD 2010–03–05 required, for the upper chords of the upper deck floor beam of section 41, an inspection for cracking of certain fastener holes, and corrective action if necessary; and repetitive replacements of the upper chords, straps (or angles), and radius fillers of certain upper deck floor beams and, for any replacement that is done, inspections for cracking, and corrective actions if necessary. This new AD adds repetitive inspections of the upper chords of the upper deck floor beam of Section 42, repetitive replacements of the upper chords, post-replacement inspections, and corrective actions if necessary. This new AD also adds post-replacement inspections for section 41 and reduces certain compliance times. This AD was prompted by a determination that the upper deck floor beams are subject to widespread fatigue damage (WFD), the existing inspection program is not sufficient to maintain an acceptable level of safety, and the upper chords of the upper deck floor beam of section 42 are subject to the unsafe condition. We are issuing this AD to detect and correct cracking of the upper chords and straps (or angles) of the floor beams, which
could lead to failure of the floor beams and consequent loss of controllability, rapid decompression, and loss of structural integrity of the airplane.

**DATES :**  This AD is effective November 7,

2014.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 7, 2014.

**ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.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–2014– 0283; 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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington,

DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Roger Caldwell, Aerospace Engineer, Technical Operations Center, ANM– 100D, FAA, Denver Aircraft Certification Office (ACO), 26805 East 68th Avenue, Room 214, Denver, CO 80249; phone: 303–342–1086; fax: 303– 342–1088; email: roger.caldwell@ faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2010–03–05, Amendment 39–16188 (75 FR 5692, February 4, 2010). AD 2010–03–05 applied to all The Boeing Company
Model 747–200C and –200F series airplanes. The NPRM published in the Federal Register on May 28, 2014 (79 FR 30486). The NPRM was prompted by a determination that the upper deck floor beams are subject to WFD, the existing inspection program is not sufficient to maintain an acceptable level of safety, and the upper chords of the upper deck floor beams in section 42 are subject to the identified unsafe condition. The NPRM proposed to add post-replacement inspections for section 41 and reduce certain compliance times. The NPRM also proposed to add repetitive inspections of the upper chords of the upper deck floor beams in section 42, repetitive replacements of the upper chords, post-replacement inspections, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the upper chords and straps (or angles) of the floor beams, which could lead to failure of the floor beams and consequent loss of controllability, rapid decompression, and loss of structural integrity of the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. We
have considered the comment received. Boeing stated that it concurs with the contents of the NPRM (79 FR 30486, May 28, 2014).

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 30486, May 28, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 30486, May 28, 2014).

Costs of Compliance

We estimate that this AD affects 25 airplanes of U.S. registry.