### 51491 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules

between fuselage station 655 and station
1434 that has a scribe line 0.001 inch or deeper.

(ii) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)) of any skin panel common to a stringer lap splice between fuselage station
655 and station 1434 that has a scribe line 0.001 inch or deeper.

(iii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S–14L/R lap splices between fuselage station 655 and station

1434.

(iv) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer lap splices.

(3) Inspection ‘‘C’’ includes the inspections for scribe lines and cracks specified in paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD on stringer S–14L/R lap splice between fuselage station 655 and station 1434 on both sides of the airplane.

(i) A detailed inspection for scribe lines. If any scribe line is found during the inspection required by this paragraph, the actions include the inspections specified in paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this

AD.

(A) A detailed inspection for cracks of the scribe line area(s).

(B) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)).

(ii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer lap splices between fuselage station 655 and station 1434.

(iii) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer S–14L/R lap splices.

(h) Exceptions to Service Information Specifications

(1) Where Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance
time ‘‘after the effective date of this AD.’’

(2) If, during accomplishment of any inspection required by this AD, any condition is found for which Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, specifies to contact Boeing for special repair instructions or supplemental instructions for the modification, and specifies that action as ‘‘RC’’ (Required for Compliance): Before further flight, do the repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD.

(i) Lap Splice Modification

At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, datedOctober 10, 2014: Do the left-side and rightside lap splice modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. (j) Post-Modification Inspections and

Corrective Action

At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014: Do a post-modification internal surface HFEC inspection for skin cracks in the modified lap splices on both sides of the airplane; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the modified lap splices thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 777–53A0052, dated October 10, 2014.

(k) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may
be emailed to: 9–ANM–Seattle–ACO–AMOC– Requests@faa.gov.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) Except as required by paragraph (h)(2)
of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(l) Related Information

(1) For more information about this AD, contact Haytham Alaidy, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6573; fax: 425–917–6590; email: Haytham.Aaidy@faa.gov.

(2) 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.

Issued in Renton, Washington, on August

17, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–20853 Filed 8–24–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3147; Directorate Identifier 2014–NM–094–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. This proposed AD would require an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. This proposed AD would also provide for optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane.


### 51492 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules

**DATES :**  We must receive comments on this proposed AD by October 9, 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: Deliver to Mail
address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed 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. It is also available
on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–

3147.

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– 3147; 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 Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Eric Lin, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6412; fax: 425– 917–6590; email: Eric.Lin@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2015–3147; Directorate Identifier 2014– NM–094–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 because of 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

We have received reports of fractured forward attach fittings of the inboard flap outboard aft flap track, and it is
believed to be the result of corrosion pits forming on the inside diameter of the fittings. Four operators have reported finding four fractured forward attach fittings of the aft flap track of the inboard flap on airplanes with approximately 20,300 to 31,900 total flight hours and approximately 5,900 to 8,500 total flight cycles. In addition, two operators reported three cracked fittings on airplanes with approximately 29,300 to 35,700 total flight hours and approximately 5,200 to 7,900 total flight cycles. This condition, if not corrected,
could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane.

Related Service Information Under 1

CFR Part 51

We reviewed Boeing Special
Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5,
2014. The service information describes procedures for an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would eliminate the need for the inspections. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified
in the **ADDRESSES** section of this NPRM.

FAA’s Determination

We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.

Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in
the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD
and the Service Information.’’ Refer to
this service information for details on the procedures and compliance times.

Explanation of ‘‘RC’’ Steps in Service
Information

The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps
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 steps identified as Required for Compliance (RC) in any
service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe
condition.

For service information that contains steps that are labeled as RC, the following provisions apply: (1) the steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

Differences Between This Proposed AD
and the Service Information

Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, specifies groups 1, 2, 3, 4, and 5 airplanes as the effectivity. However, this proposed AD is applicable only to groups 1, 2, and 4 airplanes (Model 777–200, –200LR, –300, and –300ER airplanes) because the identified unsafe condition only affects these airplanes. For groups 3 and 5 airplanes (Model 777F airplanes), the


### 51493 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules

consequence of fitting fracture on these airplanes has not been determined to be
an unsafe condition at this time. Therefore, we are not requiring inspections for groups 3 and 5 airplanes. We have coordinated this difference with Boeing. Costs of Compliance
We estimate that this proposed AD affects 148 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:



### E STIMATED 

### COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection to determine the

part number. 3 work-hours × $85 per hour = $255. $0 $255 ........................................ $37,740.

Additional Inspections ............. Up to 7 work-hours × $85 per hour = $595, per cycle. 0 Up to $595, per cycle ............. Up to $88,060, per cycle.

We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. The nested bushing installation of the attach fitting and the fitting replacement are also optional terminating actions. We have no way of determining the number of aircraft on which these actions might be
done.



### O N 

### -CONDITION 

### COSTS

Action Labor cost Parts cost Cost per product

Nested bushing installation of the attach fitting ................ 40 work-hours × $85 per hour = $3,400 .......................... $45 $3,445. Fitting replacement ........................................................... 73 work-hours × $85 per hour = $6,205 .......................... 7,400 13,605.

According to the manufacturer, all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our

cost estimate.

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**

■ 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):

The Boeing Company: Docket No. FAA– 2015–3147; Directorate Identifier 2014–

NM–094–AD.

(a) Comments Due Date

We must receive comments by October 9,

2015.

(b) Affected ADs

None.

(c) Applicability

This AD applies to all The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any
category.

(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. We are issuing this

AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane.


### 51494 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules

(f) Compliance

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

(g) Inspection To Determine the Part Number

At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014, except as provided by paragraph (l) of this AD: Do an inspection of the inboard flap of the main flap for affected part and serial numbers, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the inboard flap can be conclusively determined from
that review.

(h) Additional Inspections

If any inboard flap of the main flap having an affected part number and serial number is found during the inspection required by paragraph (g) of this AD: Except as provided by paragraph (l) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, do the inspections specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, until a terminating action in paragraph (k)(1), (k)(2), or (k)(3) of this AD is done.

(1) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and a high frequency eddy current inspection for cracking, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5,

2014.

(2) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and an ultrasound inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014.

(i) Corrective Action for Bushing Migration

If any bushing migration but no cracking is found during any inspection required by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, do the actions specified in paragraphs (i)(1) through (i)(3) of this AD. Accomplishment of a terminating action specified in paragraph (i)(3) or (k) of this AD terminates the actions required by this paragraph.

(1) Apply corrosion inhibiting compound BMS 3–23, Type II, around the bushing flanges on each side of the fitting, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014. Re-apply the corrosion inhibiting compound at the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5,

2014.

(2) Repeat the inspections specified in paragraph (h)(1) or (h)(2) of this AD, except inspect for cracking only.

(3) Do a terminating action specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of
this AD.

(i) Install a nested bushing to the forward attach fitting of the aft flap track of the inboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014.

(ii) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5,

2014.

(iii) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014.

(j) Corrective Actions for Cracking

If any cracking is found during any inspection required by paragraph (h) or (i)(3) of this AD: At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014, do a terminating action specified in paragraph (j)(1) or (j)(2) of this AD. Replacement of the forward attach fitting as specified in paragraph (j)(1) or (j)(2) of this
AD terminates the actions in this AD.

(1) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5,

2014.

(2) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57– 0094, Revision 1, dated November 5, 2014.

(k) Optional Terminating Actions

(1) Installation of the nested bushing to the forward attach fitting of the aft flap track of the inboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD.

(2) Replacement of the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD. (3) Replacement of the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD.

(l) Exception to the Service Information

Where Boeing Special Attention Service Bulletin 777–57–0094, Revision 1, dated November 5, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance
time after the effective date of this AD.

(m) Credit for Previous Actions

(1) This paragraph provides credit for the actions specified in paragraphs (h)(1) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–57–0094, dated January 29, 2014, which is not incorporated by reference
in this AD.

(2) This paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Multi Operator Message MOM–MOM–13– 0137–01B, dated February 21, 2013, which is not incorporated by reference in this AD.

(n) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (o)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.

(2) 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(4)(i) and (n)(4)(ii) apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance


### 51495 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules

or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(o) Related Information

(1) For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–917–6412; fax: 425–917– 6590; email: Eric.Lin@faa.gov.

(2) 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.

Issued in Renton, Washington, on August

17, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–20835 Filed 8–24–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3607; Directorate Identifier 2015–CE–010–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; M7 Aerospace LLC Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA26–AT, SA226–T, SA226–AT, SA226–T(B), SA226–TC, SA227–AT, SA227–TT, SA227–AC (C–26A), SA227–BC (C– 26A), SA227–CC, and SA227–DC (C– 26B) airplanes. This proposed AD was prompted by information that the airplane flight manual (AFM) does not provide adequate guidance in the handling of engine failures, which may lead to reliance on the negative torque system (NTS) for reducing drag. This condition could lead the pilot to not fully feather the propeller with consequent loss of control. This proposed AD would require inserting updates into the airplane flight manual (AFM) and/or the pilot operating handbook (POH) that will clearly establish that the NTS is not designed to automatically feather the propeller but only to provide drag protection. We are proposing this AD to correct the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by October 9, 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: Deliver to Mail
address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766;

Internet: http://www.elbitsystemsus.com; email: MetroTech@ M7Aerospace.com. You may view this
referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329–

4148.

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– 3607; 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 Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Michael Heusser, Aerospace Engineer, FAA, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5038; fax: (817) 222–5960; email: Michael.A.Heusser@faa.gov.

**SUPPLEMENTARY INFORMATION :**  Comments Invited
We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to
an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2015–3607; Directorate Identifier 2015– CE–010–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 because of 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 FAA received a report of an accident where an M7 Aerospace LLC Model SA227–AC airplane experienced left engine power loss and consequent loss of control. Training manuals provide descriptions of the negative torque system (NTS), which provides partial anti-drag protection if a negative torque condition is sensed. This feature might cause pilots to assume the system automatically provides full anti-drag protection in the event of an engine failure or power loss. The pilot must also take prompt action to fully feather the propeller on the failed engine to reduce drag. A pilot’s sole reliance on the NTS for reducing drag in the event of engine power loss may result in the pilot’s failure to initiate the Engine Failure Inflight checklist and feather the propellers in time.

This condition, if not corrected, could
result in loss of control of the aircraft due to excessive asymmetric drag.

Related Service Information Under 1

CFR Part 51

We reviewed the following M7 Aerospace LLC AFM revisions:

• AFM revision dated May 14, 2015, section III, SA26–AT Dash One;

• AFM revision dated May 14, 2015, section III, SA26–AT Dash Two;

• AFM revision B–33, sections i and III, SA226–AT, dated November 14,

2014;

• AFM revision A–29, sections i and III, SA226–T, dated November 14, 2014;

• AFM revision B–29, sections i and 3, SA226–T(B), dated November 14,

2014;

• AFM revision A–43, sections i and III, SA226–TC, dated November 14,

2014;