Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations 19811

Issued in Fort Worth, Texas, on April 24,

1996.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 96–10870 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–27–AD; Amendment 39–

9443; AD 95–24–13]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Aircraft Limited HP137 Mk1, Jetstream

Series 200, and Jetstream Models 3101

and 3201 Airplane; Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This action makes a

correction to Airworthiness Directive

(AD) 95–24–13 concerning Jetstream

Aircraft Limited (JAL) HP137 Mk1,

Jetstream Series 200, and Jetstream

Models 3101 and 3201 airplanes, which

published in the Federal Register on

December 22, 1995 (60 FR 246). That

publication incorrectly references the

number of aileron mounting spigot nut

assemblies to be replaced on the wings

of the airplanes. The AD currently

requires ‘‘replacing the securing nut

assemblies and split pins with new

special nut assemblies (Part No. SL5022

(Qty. 2))’’. The intent of the AD is to

require replacement of 2 special nut

assemblies on each wing, for a total of

4 nut assemblies. The Final Rule AD did

not specify ‘‘each wing’’, and stated that

only 2 nut assemblies rather than 4 nut

assemblies are required. This action

corrects the AD to reflect this change.

EFFECTIVE DATE: January 17, 1996.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

January 17, 1996.

FOR FURTHER INFORMATION CONTACT: Ms.

Dorenda Baker, Program Officer,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

508.2715; facsimile (322) 230.6899; or

Mr. Jeffrey Morfitt, Project Officer,

Small Airplane Directorate, Aircraft

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: On

November 17, 1995, the Federal

Aviation Administration (FAA) issued

AD 95–24–13, Amendment 39–9443 (60

FR 246, December 22, 1995), which

applies to JAL HP 137 Mk1, Jetstream

series 200, and Jetstream Models 3101

and 3201 airplanes. This AD requires

inspecting (one-time) the threaded

portion of the aileron mounting spigots

for cracks, replacing any cracked

spigots, and replacing the securing nut

assemblies with newly designed special

nut assemblies and new split pins.

Need for the Correction

The AD incorrectly references the

quantity of special nut assemblies,

inferring that a quantity of 2 assemblies

be replaced without indicating that the

2 assemblies on each wing (left wing

and right wing) should be replaced.

Correction of Publication

Accordingly, the publication of

December 22, 1995 (60 FR 246) of

Amendment 39–9443; AD 95–24–13,

which was the subject of FR Doc. 95–

66485, is corrected as follows:

§ 39.13 [Corrected]

On page 66486, in the third column,

section 39.13, paragraph (a), line 1

through line 4, replace ‘‘Inspect the

mounting spigots for cracks using both

visual and fluorescent dye penetrant

methods in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

* * *’’ with ‘‘Inspect the left and right

wing mounting spigots for cracks using

both visual and fluorescent dye

penetrant methods in accordance with

the ACCOMPLISHMENT

INSTRUCTIONS * * *’’.

On page 66486, in the third column,

section 39.13, paragraph (a)(2), line 1

through line 5, replace ‘‘Prior to further

flight, replace the securing nut

assemblies and split pins with new

special nut assemblies (Part No.

SL45022 (Qty. 2)), * * *’’ with ‘‘Prior to

further flight, replace the securing nut

assemblies and split pins on both wings

with new special nut assemblies (Part

No. SL45022 (Qty. of 2 on each wing,

total Qty. of 4 nut assemblies needed)),

* * *’’.

Action is taken herein to clarify this

requirement of AD 95–24–13 and to add

this AD correction to section 39.13 of

the Federal Aviation Regulations (14

CFR 39.13). The effective date remains

January 17, 1996.

Issued in Kansas City, Missouri on April

17, 1996.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 96–11031 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–CE–37–AD; Amendment 39–

9608; AD 96–10–03]

[RIN 2120–AA64]

Airworthiness Directives; The New

Piper Aircraft, Inc. (Formerly Piper

Aircraft Corporation) PA28, PA32,

PA34, and PA44 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain The New Piper

Aircraft, Inc. (Piper) PA28, PA32, PA34,

and PA44 series airplanes. This action

will require inspecting and modifying

the flap lever assembly. Reports of worn

flap handle attach bolts and elongated

holes in the flap lever to cable mounting

attach point prompted this AD action.

The actions specified by this AD are

intended to prevent failure of the flap

handle attach bolt and sudden retraction

of the flaps, which, if not detected and

corrected, could result in loss of control

of the airplane.

DATES: Effective June 14, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 14,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

The New Piper Aircraft, Inc., Attn:

Customer Service, 2629 Piper Dr., Vero

Beach, Florida 32960. This information

may also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket 95–

CE–37–AD, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Christina Marsh, Aerospace Engineer,

FAA, Atlanta Aircraft Certification

Office, Campus Building, 1701

Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7362; facsimile (404) 305–

7348.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to The

New Piper Aircraft, Inc. (Piper) PA28,

PA32, PA34, and PA44 series airplanes

was published in the Federal Register

on October 13, 1995 (60 FR 53314). The

action proposed to require inspecting
19812 Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations

and modifying the flap lever assembly.

Accomplishment of the proposed action

would be in accordance with Piper

Service Bulletin (SB) No. 965, dated

September 1, 1993.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to each

comment received from two

commenters.

The first commenter recommends that

the compliance time be changed to

apply to aircraft with greater than 2,000

hours time-in-service (TIS) and require

these aircraft to accomplish the

modification within the next 500 hours

TIS or 12 calendar months, whichever

occurs first. The commenter

acknowledges that the wear problem in

the flap handle attach area is a

widespread problem and has been dealt

with by the industry for years.

Industry’s experience with the problem

is that it progresses gradually over time;

therefore, the immediacy of the 100

hour TIS compliance time does not

seem warranted. The commenter

recommends the compliance time be

changed to 500 hours TIS to coincide

with commercial operators’ inspection

cycles and 12 calendar months to

coincide with an individual owner/

operator’s annual inspection.

The FAA recognizes the commenter’s

proposal, but the service difficulty

reports reflect 73 reports from January

1990 to March 1995 and from these 73

reports, 50 reports were submitted from

the same commercial operator. The

operator submitted a TIS range of 1200

to 2400 hours TIS for the 50 occurrences

in their fleet. The remaining 23 reports

contain TIS values ranging from 1884 to

5063. With this information, FAA could

not determine the statistical distribution

or fleet average. Subsequently, the FAA

made a determination that a compliance

time with a 2,000 hour TIS threshold or

within the next 100 hours TIS for those

airplanes with greater than 2,000 hours

TIS was reasonable and will not impose

an undue burden on the affected

owners/operators. The compliance time

remains unchanged as a result of the

comment.

The second commenter recommended

that the standard part designation

corresponding to the manufacturer’s

part number be included in the AD. The

standard part designation is typically

listed in the manufacturer’s service

publications and manuals.

The commenter also states that the

AD as proposed requires the installation

of the Piper part numbers to comply

with the AD. The Piper part numbers (P/

N) are equivalent to the standard parts

and therefore, the standard parts

designation should also be listed as

acceptable compliance to this AD

action.

The FAA concurs that the standard

parts are equivalent to the Piper parts

designated in this AD, with the

exception of the bushing, Piper P/N

63900–174. The standard parts

designation will be listed as equivalent

parts in the Final Rule to permit AD

compliance (with the exception of the

bushing, Piper P/N 63900–174).

The commenter also states that P/N

407 564 was listed incorrectly in the

NPRM as P/N 407 584. The FAA

concurs and the part number is

corrected in the Final Rule.

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

The FAA estimates that 30,000

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 2 workhours per airplane

to accomplish this action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $16

per airplane. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $4,080,000.

This figure is based on the assumption

that all of the affected airplanes have

worn bolts and elongated holes and that

none of the owners/operators of the

affected airplanes have replaced the

worn parts.

Piper has informed the FAA that parts

have been distributed to equip

approximately 8,000 airplanes.

Assuming that these distributed parts

are incorporated on the affected

airplanes, the cost of the proposed AD

will be reduced by $1,088,000 from

$4,080,000 to $2,992,000.

The regulations adopted herein will

not have substantial direct effects 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. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (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); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

96–10–03 The New Piper Aircraft, Inc.

(formerly Piper Aircraft Corporation):

Amendment No. 39–9608; Docket No.

95–CE–37–AD.

Applicability: The following airplane

models and serial numbers, certificated in

any category:

Models Serial numbers

PA28–140 ........................................................... 28–20000 through 28–26946 and 28–7125001 through 28–7725290.

PA28–150, PA28–160, and PA28–180 .............. 28–1 through 28–5859, 28–7105001 through 28–7505259, 28–E13, and 28–03.

PA28–151 ........................................................... 28–7415001 through 28–7715314.

PA28–161 ........................................................... 28–7716001 through 28–8616057, 2816001 through 2816102, and 2841001 through 2841346.

PA28–181 ........................................................... 28–7690001 through 28–8690062 and 2890001 through 2890169.
Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations 19813

Models Serial numbers

PA28–235 ........................................................... 28–10001 through 28–11378, 28–7110001 through 28–7710089, and 28–E11.

PA28–236 ........................................................... 28–7911001 through 28–8611008 and 2811001 through 2811034.

PA28–201T ......................................................... 28–7921001 through 28–7921095.

PA28R–180 ......................................................... 28R–30001 through 28R–31270 and 28R–7130001 through 28R–7130013.

PA28R–200 ......................................................... 28R–35001 through 28R–35820 and 28R–7135001 through 28R–7635462.

PA28R–201 ......................................................... 28R–7737001 through 28R–7837319 and 2837001 through 2837059.

PA28R–201T ....................................................... 28R–7703001 through 28R–7803374 and 2803001 through 2803012.

PA28RT–201 ....................................................... 28R–7918001 through 28R–8218026.

PA28RT–201T .................................................... 28R–7931001 through 28R–8631005 and 2831001 through 2831038.

PA32–260 ........................................................... 32–1 through 32–1297 and 32–7100001 through 32–7800008.

PA32–300 ........................................................... 32–40000 through 32–40974 and 32–7140001 through 32–7940290.

PA32–301 ........................................................... 32–8006001 through 32–8406020.

PA32–301T ......................................................... 32–8024001 through 32–8424002.

PA32R–300 ......................................................... 32R–7680001 through 32R–7880068.

PA32RT–300 ....................................................... 32R–7885001 through 32R–7985105.

PA32RT–300T .................................................... 32R–7887001 through 32R–7987126.

PA32R–301 ......................................................... 32R–8013001 through 32R–8413024.

PA32R–301T ....................................................... 32R–8029001 through 32R–8429028.

PA34–200 ........................................................... 34–7250001 through 34–7450220.

PA34–200T ......................................................... 34–7570001 through 34–8170092.

PA34–220T ......................................................... 34–8133001 through 34–8233088.

PA44–180 ........................................................... 44–7995001 through 44–8195026 and 4495001 through 4495013.

PA44–180T ......................................................... 44–8107001 through 44–8107066.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (f) of this AD. The

request should include an assessment of the

effect of the modification, alteration, or repair

on the unsafe condition addressed by this

AD; and, if the unsafe condition has not been

eliminated, the request should include

specific proposed actions to address it.

Compliance: Required upon the

accumulation of 2,000 hours time-in-service

(TIS) or within the next 100 hours TIS after

the effective date of this AD, whichever

occurs later, unless already accomplished.

Note 2: The compliance time specified in

this AD takes precedence over the

compliance time specified in the The New

Piper Aircraft Inc. (Piper) Service Bulletin

(SB) 965, dated September 1, 1993.

Note 3: The instructions in this AD do not

mirror the Piper service bulletin and

instructions in this AD take precedence over

the service bulletin instructions. This AD

will require installing the clevis bolt,

regardless of the condition of the current

part.

To prevent failure of the flap handle attach

bolt and sudden retraction of the flaps,

which, if not detected and corrected, could

result in loss of control of the airplane,

accomplish the following:

(a) Measure the cable mounting attach hole

diameter and enlarge the hole to .316 of an

inch diameter. If the diameter of the cable

mount attach hole is larger than .316 of an

inch, prior to further flight, replace the flap

lever handle (refer to the applicable

illustrated parts catalog for part number), in

accordance with the INSTRUCTIONS section

of Piper SB No. 965, dated September 1,

1993.

(b) Install a new bushing (using only Piper

Part Number (P/N) 63900–174) into the cable

mounting attach hole, in accordance with the

INSTRUCTIONS section of Piper SB No. 965,

dated September 1, 1993.

(c) Replace the flap lever handle attach bolt

with a new clevis bolt (Piper P/N 400 673 or

standard P/N AN23–11) in accordance with

the INSTRUCTIONS section of Piper SB No.

965, dated September 1, 1993.

(d) Inspect the washer, nut, and cotter pin,

and if damaged, prior to further flight,

replace washer (Piper P/N 407–564 or

standard P/N AN960–10), nut (Piper P/N

404–392 or standard P/N AN320–3), and

cotter pin (Piper P/N 424–051 or standard P/

N MS24665–132) as applicable in accordance

with the INSTRUCTIONS section of Piper SB

No. 965, dated September 1, 1993.

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(f) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, FAA, Atlanta

Aircraft Certification Office, Campus

Building, 1701 Columbia Avenue, suite 2–

160, College Park, Georgia 30337–2748. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Atlanta Aircraft Certification

Office.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta Aircraft

Certification Office.

(g) The inspections and replacements

required by this AD shall be done in

accordance with The New Piper Aircraft Inc.

Piper Service Bulletin No. 965, dated

September 1, 1993. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from The New Piper Aircraft, Inc.,

Attn: Customer Service, 2629 Piper Dr., Vero

Beach, Florida 32960. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106, or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(h) This amendment (39–9608) becomes

effective on June 14, 1996.

Issued in Kansas City, Missouri, on April

26, 1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–10911 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–CE–51–AD; Amendment 39–

9606; AD 96–10–01]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. (Formerly Piper

Aircraft Corporation) Models PA–28–

140, PA–28–150, PA–28–160, and PA–

28–180 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain The New Piper

Aircraft, Inc. (Piper) Models PA–28–

140, PA–28–150, PA–28–160, and PA–

28–180 airplanes. This action requires a