This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final
rules. 

# Proposed Rules Federal Register 

### 78726

Vol. 79, No. 250

Wednesday, December 31, 2014

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–1093; Directorate Identifier 2014–CE–035–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; British Aerospace Regional Aircraft Airplanes** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for British Aerospace Regional Aircraft Model Jetstream Series 3101 and Jetstream Model 3201 airplanes that would supersede AD 2014–06–03. This proposed 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 stress corrosion cracking of the main landing gear spigot housing. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by February 17, 2015.

**ADDRESSES :**  You may send comments 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 proposed AD, contact BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 1292 675207, fax: +44 1292 675704; email: RApublications@baesystems.com;

Internet: http:// www.jetstreamcentral.com. You may review copies of the 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–2014– 1093; 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 (telephone (800) 647–5527) is in the

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

**FOR FURTHER INFORMATION CONTACT :**  Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4138; fax: (816) 329–4090; email: taylor.martin@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2014–1093; Directorate Identifier 2014–CE–035–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:// 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

On March 14, 2014, we issued AD 2014–06–03, Amendment 39–17807 (79 FR 17395; March 28, 2014) (‘‘AD 2014– 06–03’’). That AD required actions
intended to address an unsafe condition on British Aerospace Regional Aircraft Model Jetstream Series 3101 and Jetstream Model 3201 airplanes and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country.

Since we issued AD 2014–06–03, corrosion was found on an airplane at the top outer edge of the forward spigot housing and extended along the top of the spigot housing. BAE Systems (Operations) Limited issued new service information to ensure the spigot cap is positioned correctly and to include inspection instructions for movement of the special washer and instructions for addressing any corrosion that may be
found.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2014–0239, dated November 3, 2014 (referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the specified products. The MCAI states:

Several cases of stress corrosion cracking of DTD 5094 standard Main Landing Gear (MLG) cylinders have been reported on Jetstream Series 3200 and 3100 aeroplanes. Prompted by these findings, The United Kingdom (UK) Civil Aviation Authority (CAA) issued AD 003–01–86 to require visual and non-destructive testing (NDT) inspections of the MLG assembly cylinder attachment spigot housing in accordance with BAE Systems (Operations) Ltd SB 32– A–JA851226. In 2012 an additional occurrence of Jetstream 3100 MLG failure after landing was reported, the subsequent investigation revealed stress corrosion cracking of the yoke pintle housing as a root cause of the MLG failure. Consequently EASA issued EASA AD 2013–0208 to require inspection of the MLG in accordance with BAE Systems (Operations) Ltd SB 32–A– JA851226 Revision 5 or later approved revisions to detect any crack, however, SB 32–A–JA851226 did not apply to aeroplanes


### 78727 Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules

equipped with MLG cylinders manufactured from L161 material, since that is not susceptible to stress corrosion, BAE Systems (Operations) Ltd issued SB 32–JM7862 to address degradation of the surface protection by placing a special washer over the forward face of the MLG spigot housing, which rotates with the spigot housing. EASA issued AD 2013–0206 to require modification of the left (LH) and right hand (RH) MLG in
accordance with this SB. In 2014 a further event was reported, where the LH MLG of a Jetstream 3100 aeroplane collapsed during landing, this resulted in the aeroplane departing from the runway. The accident is still under investigation by the UK Air Accident Investigation Branch. Preliminary results of the investigation determined that cracking, which caused the MLG collapse, was initiated from a corrosion pit at the top outer edge of the forward spigot housing and extended along the top of the spigot housing. The spigot housing material
was DTD 5094. The affected LH MLG had
been modified in accordance with BAE Systems (Operations) Ltd SB 32–JM7862 Revision 1. Further investigation discovered that the instructions provided in BAE Systems (Operations) Ltd SB 32–JM7862 Revision 1 did not effectively prevent stress corrosion cracking because, under certain circumstances, it allows the rotation of the special washer and consequent damage of the end face of the spigot housing. This condition, if not corrected, could lead to structural failure of the MLG, possibly resulting in loss of control of the aeroplane during take-off or landing runs. To address this potential unsafe condition, BAE Systems (Operations) Ltd issued SB 32– JM7862 Revision 2 to clarify the orientation of the spigot bearing cap, later revised to SB 32–JM7862 Revision 3 to ensure the spigot bearing cap is correctly positioned. Additionally, BAE Systems (Operations) Ltd issued SB 32–A–JA140940 to provide inspection instructions to detect migration of the special washer and any potential corrosion resulting from that unwanted migration for MLG installations modified earlier in accordance with BAE Systems (Operations) Ltd SB 32–JM7862 up to

Revision 2.
For the reasons described above, this AD partially retains the requirements of EASA AD 2013–0206, which is superseded, and requires a one-time inspection of pre-SB 32– JM7862 Revision 3 MLG installations and, depending on findings, applicable corrective action(s). You may examine the MCAI on the

Internet at http://www.regulations.gov by searching for and locating Docket No.

FAA–2014–1093.

Relevant Service Information

British Aerospace Regional Aircraft has issued British Aerospace Jetstream
Series 3100 and 3200 Service Bulletin No. 32–JM7862, Revision 3, dated October 3, 2014; and British Aerospace Jetstream Series 3100 and 3200 Service Bulletin No. 32–A–JA140940, Original Issue, dated October 3, 2014. The actions described in this service
information are intended to correct the
unsafe condition identified in the

MCAI.

FAA’s Determination and Requirements of the Proposed AD

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

Costs of Compliance

We estimate that this proposed AD will affect 44 products 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 proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $170 per product.

Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $14,960, or $340 per product.

We accept modification of the MLG,
if done before the effective date of this proposed AD, using earlier versions of the service information. However, the
earlier versions of the service information require additional inspections with possible corrective

actions.

In addition, we estimate that any necessary follow-on actions that may be required if using an earlier version of
the service information would take about 1 work-hour to inspect for special washer migration and corrosion damage and require parts costing $100 for replacement of the special washer and application of witness paint, if necessary, for a cost of $185 per product. We have no way of determining the number of products that may need these actions.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking

action.

Regulatory Findings

We determined that this proposed AD would not have federalism implications
under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this proposed regulation:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866,

(2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska, and

(4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

**PART 39—AIRWORTHINESS**
**DIRECTIVES**

■ 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 removing Amendment 39–17806 (79 FR 17395; March 28, 2014), and adding the following new AD:

British Aerospace Regional Aircraft: Docket No. FAA–2014–1093; Directorate
Identifier 2014–CE–035–AD.


### 78728 Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules

(a) Comments Due Date

We must receive comments by February

17, 2015.

(b) Affected ADs

This AD supersedes AD 2014–06–03, Amendment 39–17806 (79 FR 17395; March 28, 2014).

(c) Applicability

This AD applies to British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes, all serial numbers, certificated in any category.

(d) Subject

Air Transport Association of America (ATA) Code 32: Landing Gear.

(e) Reason

This AD was prompted by 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 stress corrosion cracking of the main landing gear (MLG) spigot housing. We are issuing this AD to prevent corrosion cracking of the MLG spigot housing. This condition, if not corrected, could cause structural failure of the MLG resulting in loss of control of the airplane during take-off or landing.

(f) Actions and Compliance

Unless already done, do the following actions in paragraphs (f)(1) through (f)(11), including all subparagraphs, as applicable.

(1) At the next scheduled MLG removal, modify the installation of the left hand (LH) and right hand (RH) MLG at the forward spigot following British Aerospace Jetstream
Series 3100 and 3200 Service Bulletin No. 32–JM7862, Revision 3, dated October 3,

2014.

Note to paragraph (f)(1) of this AD: The next scheduled MLG removal may be for non-destructive testing or overhaul, as applicable.

(2) If done before the effective date of this AD, we will accept modification of the LH or RG MLG following British Aerospace Jetstream Series 3100 & 3200 Service Bulletin SB 32–JM7862, Revision 2, dated June 13, 2014; or British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JM7862, Revision 1, dated May 7, 2013, for compliance with paragraph (f)(1) of this AD.

(3) For airplanes that, before the effective date of this AD, have been modified following British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JM7862, Revision 2, dated June 13, 2014, visually inspect the LH and RH MLG to detect migration of a special washer following the instructions in Part 1 of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA140940, Original Issue, dated October 3, 2014, at the compliance time listed in paragraph (f)(3)(i) or (f)(3)(ii) of this AD, as applicable.

(i) For MLG configuration equipped with DTD5094 cylinder: Within the next 200 flight cycles after the effective date of this AD or
within the next 2 months after the effective date of this AD, whichever occurs first. (ii) For MLG configuration equipped with L161 cylinder: Within the next 600 flight cycles after the effective date of this AD or
within the next 6 months after the effective date of this AD, whichever occurs first.

(4) If evidence of migration of the special washer was detected during the inspection required in paragraph (f)(3) of this AD, within the applicable compliance time specified in paragraph (f)(3)(i) or (f)(3)(ii) of this AD, do the corrective actions on the LH or RH MLG, as applicable, following Part 2 of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA140940, Original Issue, dated October 3, 2014.

(5) If no evidence of migration of the special washer was detected during the inspection required in paragraph (f)(3) of this AD, before further flight, apply a witness paint over the special washer tab and onto the MLG spigot housing (LH and RH MLG) following Part 1 of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA140940, Original Issue, dated October 3, 2014.

(6) For airplanes that, before the effective date of this AD, have been modified following British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JM7862, Revision 1, dated May 7, 2013, do all of the actions on the MLG cylinder (LH and/or RH, as applicable) following the instructions in Part 2 of British Aerospace Jetstream Series
3100 & 3200 Service Bulletin 32–A– JA140940, Original Issue, dated October 3, 2014, at the compliance time listed in paragraph (f)(6)(i) or (f)(6)(ii), as applicable.

(i) For MLG configuration equipped with DTD5094 cylinder: Within the next 200 flight cycles after the effective date of this AD or
within the next 2 months after the effective date of this AD, whichever occurs first.

(ii) For MLG configuration equipped with L161 cylinder: Within the next 600 flight cycles after the effective date of this AD or
within the next 6 months after the effective date of this AD, whichever occurs first.

(7) If any wear, corrosion, or damage is detected during the inspection required in either paragraph (f)(3) or (f)(6), as applicable, of this AD, before further flight, do all of the corrective actions (including application of the a witness paint) following the instructions in Part 2 of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA140940, Original Issue, dated October 3, 2014.

(8) Between 30 and 45 days after doing the action required in either paragraph (f)(3) or (f)(6) of this AD or between the next 20 to 30 flight cycles after doing the action required in either paragraph (f)(3) or (f)(6) of this AD, whichever occurs first, inspect the witness paint applied as required in either paragraph (f)(5) or (f)(7) of this AD following the instructions in Part 3 of British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–A–JA140940, Original Issue, dated October 3, 2014.

(9) If any damaged paint is detected during the inspection required in paragraph (f)(8) of this AD, before further flight, contact BritishAerospace Regional Aircraft to obtain FAAapproved repair instructions approved specifically for this AD and incorporate those instructions. You may find the contact information for British Aerospace Regional Aircraft in paragraph (h) of this AD.

(10) As of the effective date of this AD, do not install a LH or RH MLG on any of the applicable airplanes unless it has passed all of the inspections required by this AD.

(11) For all airplanes: The compliance times for paragraphs (f)(3)(i), (f)(3)(ii), (f)(6)(i), (f)(6)(ii), and (f)(8) of this AD are presented in flight cycles (landings). If the total flight cycles have not been kept, multiply the total number of airplane hours time-in-service (TIS) by 0.75 to calculate the cycles. You may use the following as an example for this AD:

(i) 200 hours TIS × .75 = 150 cycles; or (ii) 600 hours TIS × .75 = 450 cycles.

(g) Other FAA AD Provisions

The following provisions also apply to this

AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to ATTN: Taylor Martin, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4138; fax: (816) 329– 4090; email: taylor.martin@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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.

(h) Related Information

Refer to MCAI European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, AD No. 2014–0239, dated November 3, 2014; and British Aerospace Jetstream Series 3100 & 3200 Service Bulletin SB 32–JA851226, Revision 5, dated April 30, 2013; British Aerospace Jetstream and British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32–JM7862, Revision 1, dated May 7, 2013, for related information. You may examine the MCAI on the Internet

at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–1093. For service information related to this AD, contact BAE Systems (Operations) Ltd, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; phone: +44 1292 675207, fax: +44 1292 675704; email: RApublications@baesystems.com; Internet: http://www.jetstreamcentral.com. You may review copies of the 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.


### 78729 Federal Register / Vol. 79, No. 250 / Wednesday, December 31, 2014 / Proposed Rules

Issued in Kansas City, Missouri, on December 22, 2014.
Robert Busto, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–30631 Filed 12–30–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–1083; Directorate Identifier 2014–CE–036–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Various Aircraft Equipped With Wing Lift Struts** 

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

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

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 99–01–05 R1, which applies to certain aircraft equipped with wing lift struts. AD 99– 01–05 R1 currently requires repetitively inspecting the wing lift struts for corrosion; repetitively inspecting the wing lift strut forks for cracks; replacing any corroded wing lift strut; replacing any cracked wing lift strut fork; and repetitively replacing the wing lift strut forks at a specified time for certain airplanes. Since we issued AD 99–01–05 R1, we have determined that additional airplane models should be added to the Applicability section. This proposed AD would retain all requirements of the existing AD. We are proposing this AD
to correct the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by February 17, 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 Piper Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; Internet: www.piper.com. Copies of the instructions to the F. Atlee Dodge supplemental type certificate (STC) and information about the Jensen Aircraft STCs may be obtained from F. Atlee Dodge, Aircraft Services, LLC., 6672 Wes Way, Anchorage, Alaska 99518– 0409, Internet: www.fadodge.com. You may review copies of the 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–2014– 1083; 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 :** 

For Piper Aircraft, Inc. airplanes, contact: Gregory ‘‘Keith’’ Noles, Aerospace Engineer, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, Georgia 30337; phone: (404) 474–5551; fax: (404) 474–5606; email: gregory.noles@faa.gov.

For FS 2000 Corp, FS 2001 Corp, FS 2002 Corporation, and FS 2003 Corporation airplanes, contact: Jeff Morfitt, Aerospace Engineer, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, Washington 98057; phone: (425) 917–6405; fax: (245) 917–6590;
email: jeff.morfitt@faa.gov.

For LAVIA ARGENTINA S.A. (LAVIASA) airplanes, contact: S.M. Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4145; fax: (816) 329–4090; email: sarjapur.nagarajan@ faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments
to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2014–1083; Directorate Identifier 2014–CE–036–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

On November 22, 2013, we issued AD 99–01–05 R1, Amendment 39–17688 (78 FR 73997, December 10, 2013) and later issued on December 18, 2013 (78 FR 79599, December 31, 2013) as a correction, (‘‘AD 99–01–05 R1’’), for certain aircraft equipped with wing lift
struts. AD 99–01–05 R1 resulted from the need to clarify the intent that if a sealed wing lift strut assembly is installed as a replacement part, the repetitive inspection requirement is terminated only if the seal is never improperly broken. If the seal is improperly broken, then that wing lift strut becomes subject to continued repetitive inspections. We did not intend to promote drilling holes into or otherwise unsealing a sealed strut.

We issued AD 99–01–05 R1 to detect and correct corrosion and cracking on the front and rear wing lift struts and forks, which could cause the wing lift
strut to fail. This failure could result in the wing separating from the airplane.

Actions Since AD 99–01–05 R1 Was
Issued

Since AD 99–01–05 R1 was issued, we have been informed that Piper Aircraft, Inc. (Piper) Models J–3, J3C–65 (Army L–4A), J3P, J4B, and J4F airplanes should be added to the Applicability section. We have also
been informed that there is a serial number overlap between Piper Model
PA–18s listed in AD 99–01–05 R1 and Piper Model PA–19 (Army L–18C).
Certain serial numbers listed for Model
PA–18s should also be listed under Model PA–19 (Army L–18C).

On December 22, 1998, we issued AD 99–01–05, Amendment 39–10972 (63 FR 72132, December 31, 1998), to supersede AD 93–10–06, Amendment 39–8586 (58 FR 29965, May 25, 1993), which previously included Piper Models J–3, J3P, J4B, and J4F airplanes in the Applicability section, in order to clarify certain requirements of AD 93– 10–06, eliminate the lift strut fork