### 14704 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations

(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. 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):
2016–06–06 Quest Aircraft Design, LLC: Amendment 39–18437; Docket No. FAA–2015–5318; Directorate Identifier 2015–CE–035–AD.
(a) Effective Date

This AD is effective April 22, 2016.
(b) Affected ADs

None. (c) Applicability

This AD applies to Quest Aircraft Design, LLC Model KODIAK 100 airplanes, all serial numbers 100–0001 through 100–0149, that are certificated in any category.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 2730; Elevator Control System.
(e) Unsafe Condition

This AD was prompted by a report of limited control yoke movement due to cushion edging jammed in the elevator control anti-rotation guide slot. We are issuing this AD to prevent failure of the elevator control system, which could result in loss of control.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspect Cushion Edging

Before further flight April 22, 2016 (after the effective date of this AD) and repetitively thereafter at intervals not to exceed 50 hours time-in-service until the terminating action specified in paragraph (i) of this AD is done, inspect the cushion edging, part number (P/ N) M22529/2–3R–25, located on each side of the elevator control anti-rotation guide slot, P/N 100–619–0008, for the pilot and co-pilot control yoke assemblies, following section 5.1 Cushion Edging Inspection of Quest Aircraft Company Field Service Instruction, Elevator Control System—Cushion Edging Inspection, Report No. FSI–105, Revision 00, not dated, as specified in Quest Aircraft KODIAK Mandatory Service Bulletin SB14– 07, dated August 26, 2014; and Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015.
(h) Replace Cushion Edging

If damage or wear is found during any inspection required in paragraph (g) of this AD, before further flight, replace the cushion edging following section 5.3 of Quest Aircraft Company Field Service Instruction, Elevator Control System—Cushion Edging Inspection, Report No. FSI–105, Revision 00, not dated, as specified in Quest Aircraft KODIAK Mandatory Service Bulletin SB14–07, dated August 26, 2014; and Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015.
(i) Install Wear Pads (Terminating Action for the Repetitive Inspections)

Within 1 year after April 22, 2016 (the effective date of this AD), remove the cushion edging, P/N M22529/2–3R–25, installed on the elevator control anti-rotation guide, and install wear pads, P/N 100–619–0037, on the elevator bearing assembly link arm following section 5. Instructions, including all subsections, of Quest Aircraft Field Service Instruction, Yoke Anti-Rotation Guide Wear Pad Upgrade, Report No. FSI–108, Revision 00, not dated, as specified in Quest Aircraft KODIAK 100 Recommended Service Bulletin SB15–01, dated March 26, 2015. Installing all four wear pads on the pilot and co-pilot arms of the elevator bearing assemblies terminates the repetitive inspections required in paragraph (g) of this AD.
(j) 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 (k) 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.
(k) Related Information

For more information about this AD, contact David Herron, Aerospace Engineer, Seattle ACO, FAA, 1601 Lind Avenue SW., Renton, Washington 98057; phone: (425) 917–6469; fax: (425) 917–6591; email: david.herron@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this 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 the AD specifies otherwise.

(i) Quest Aircraft Company KODIAK 100 Mandatory Service Bulletin SB14–07, Revision 01, dated November 23, 2015.

(ii) Quest Aircraft KODIAK Mandatory Service Bulletin SB14–07, dated August 26,
2014.

(iii) Quest Aircraft Company Field Service Instruction, Elevator Control System— Cushion Edging Inspection, Report No. FSI– 105, Revision 00, not dated.

(iv) Quest Aircraft KODIAK 100 Recommended Service Bulletin SB15–01, dated March 26, 2015.

(v) Quest Aircraft Field Service Instruction, Yoke Anti-Rotation Guide Wear Pad Upgrade, Report No. FSI–108, Revision 00, not dated.

(3) For Quest Aircraft Design, LLC service information identified in this AD, contact Quest Aircraft Design, LLC, 1200 Turbine Drive, Sandpoint, Idaho 83864; telephone: (208) 263–1111; toll free: (866) 263–1112; email: CustomerService@QuestAircraft.com; Internet: www.questaircraft.com.

(4) You may view this service information at 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. In addition, you can access this service information on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–5318.

(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 Kansas City, Missouri, on March 10, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–05898 Filed 3–17–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2016–4227; Directorate Identifier 2016–NM–025–AD; Amendment**  **39–18439; AD 2016–06–08]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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


### 14705 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787–8 and 787– 9 airplanes powered by GE GEnx engines. This AD requires revising the airplane flight manual to provide the flight crew a new fan ice removal procedure to reduce the likelihood of engine damage due to fan ice shedding. This AD also requires, for certain airplanes, reworking the fan stator module assembly on GE GEnx–1B Performance Improvement Program (PIP) 2 engines. This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent reduced fan tip clearance, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines.

**DATES :**  This AD is effective March 18,
2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 18, 2016.

We must receive comments on this AD by May 2, 2016.

**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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this final rule, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@
ge.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–2016–
4227. 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–2016– 4227; 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 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 :**  Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6438; fax: 425– 917–6590; email: Suzanne.Lucier@ faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We received a report of a significant GE GEnx–1B PIP2 engine fan rub event, apparently caused by partial fan ice shedding and a resulting fan imbalance that in turn caused substantial damageto the engine and an in-flight nonrestartable power loss. We continue to investigate this issue with Boeing and GE; however, the engine damage appears to be a result of reduced fan tip clearances common to the GEnx–1B PIP2 engine. The other engine on the event airplane was a GEnx–1B PIP1 configuration that incurred expected wear and minor damage during the icing event and continued to operate normally. The event occurred in icing conditions at an altitude of 20,000 feet. Reduced fan tip clearance, if not corrected, could result in engine damage and a possible in-flight non-restartable power loss of one or both engines. We are issuing this AD to correct the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

We reviewed GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016, which describes procedures for reworking the fan stator module assembly on GEnx–1B PIP2 engines. 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.

FAA’s Determination

We are issuing 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.
AD Requirements

This AD requires accomplishing the actions specified in the GE service information described previously. This AD also requires revising the airplane flight manual (AFM) to provide the flight crew a new fan ice removal procedure to reduce the likelihood of engine damage due to fan ice shedding.

Interim Action

We consider this AD interim action. The engine manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking.
FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because reduced fan tip clearance could result in engine damage and a possible in-flight non-restartable power loss of one or both engines. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include the docket number FAA–2016–4227 and Directorate Identifier 2016–NM–025–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD.


### 14706 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations

Costs of Compliance

We estimate that this AD affects 34 airplanes of U.S. registry. We estimate the following costs to comply with this
AD:



### E STIMATED 

### COSTS

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

AFM revision .............. 1 work-hour × $85 per hour = $85 ........... $0 $85 $2,890. Rework ....................... 40 work-hours × $85 per hour = $3,400 .. 0 3,400 3,400 (1 affected airplane).

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

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 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. 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):
2016–06–08 The Boeing Company: Amendment 39–18439; Docket No. FAA–2016–4227; Directorate Identifier 2016–NM–025–AD.
(a) Effective Date

This AD is effective March 18, 2016.

(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 787–8 and 787–9 airplanes, certificated in any category, powered by General Electric (GE) GEnx engines.
(d) Subject

Air Transport Association (ATA) of America Code 72, Engines.

(e) Unsafe Condition

This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent reduced fan tip clearance, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Revision of Airplane Flight Manual (AFM): Certificate Limitations

Within 7 days after the effective date of this AD, revise the Certificate Limitations chapter of the applicable Boeing 787 AFM to include the statement provided in figure 1 to paragraph (g) of this AD. This may be done by inserting a copy of this AD into the AFM. 

### F IGURE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### THIS 

### AD

**Engine Operational Limits** Cold Weather Operations Fan Ice Removal In order to avoid possible fan damage and

engine failure, when in icing conditions above 12,500 feet MSL, the flight crewmust comply with the Cold Weather Operations Additional Fan Ice Removal procedure contained in the Operating Procedures chapter of this manual.

(h) AFM Revision: Operating Procedures

Within 7 days after the effective date of this AD, revise the Operating Procedures chapter of the Boeing 787 AFM to include the statement provided in figure 2 to paragraph (h) of this AD. This may be done by inserting a copy of this AD into the AFM.



### F IGURE 

### 2 TO 

### PARAGRAPH 

### (h) OF 

### THIS 

### AD

**Cold Weather Operations Additional Fan Ice Removal Procedure** This procedure is required when in icing conditions above 12,500 feet MSL, by the Engine Operational Limits Cold Weather Operations Fan Ice Removal limitation contained in the Certificate Limitations chapter of this manual. The language below shall not be modified. During flight in icing conditions (EAI EICAS

indication showing) with N1 settings below 85%, or when fan icing is suspected due to high engine vibration, the fan blades mustbe cleared of any ice. Do the following procedure every 5 minutes on both engines,one engine at a time: Increase to a minimum of 85% N1 momentarily, then resume normal operation.

(i) Rework

For airplanes with two engines with engine serial numbers listed in paragraph 1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016: On or before March 25, 2016, rework the fan stator module assembly of one of the engines, in accordance with paragraphs 3.A.(1)(b), 3.B., or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016.
(j) Parts Installation Limitation

As of March 25, 2016, no person may operate an airplane that has two engines with engine serial numbers listed in paragraph


### 14707 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations

1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016, unless at least one engine has been reworked in accordance with paragraph 3.A.(1)(b), 3.B., or 3.C. of the Accomplishment Instructions of GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016.
(k) Reporting Provisions

Although GE GEnx Service Bulletin GEnx– 1B 72–0309 R00, dated March 11, 2016, specifies reporting certain tip clearance measurements to GE, this AD does not require any report.
(l) 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 (m) 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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(m) Related Information

For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425– 917–6590; email: Suzanne.Lucier@faa.gov.
(n) Material Incorporated by Reference

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

(i) GE GEnx–1B Service Bulletin 72–0309 R00, dated March 11, 2016.

(ii) Reserved. (3) For service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ge.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 March 14, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2016–06117 Filed 3–17–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–AD; Amendment**  **39–18438; AD 2016–06–07]**

**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) 2006–22– 15 for all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747– 300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. AD 2006–22–15 required repetitive inspections for cracking of certain panel webs and stiffeners of the nose wheel well (NWW), and corrective actions if necessary; and replacement of certain panels with new panels, which terminates the repetitive inspections. This new AD reduces a compliance time and adds certain inspections and an applicable repair. This AD was prompted by multiple reports of fatigue cracking in the NWW top panel and side panel webs and stiffeners. We are issuing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage.

**DATES :**  This AD is effective April 22,
2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 22, 2016. **ADDRESSES :**  For service information identified in this final rule, 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–2014–
0774. 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– 0774; 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 :**  Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: Bill.Ashforth@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006) (‘‘AD 2006–22–15’’). AD 2006–22–15 applied to all The Boeing Company Model 747– 100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. The SNPRM published in the Federal Register on September 18, 2015 (80 FR 56407) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on November 17, 2014 (79 FR 68388) (‘‘the NPRM’’). The NPRM proposed to continue to require repetitive inspections for cracking of