330 Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations

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 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

94–26–14 British Aerospace Regional

Aircraft Limited (Formerly British

Aerospace Commercial Aircraft Limited,

Vickers-Armstrongs Aircraft Limited):

Amendment 39–9109. Docket 94–NM–

108–AD.

Applicability: All Model Viscount 744,

745D, and 810 series airplanes, certificated in

any category.

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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent reduced structural integrity of

the chassis, accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform a detailed visual

inspection to detect cracks in the chassis side

bracing structure and in the chassis top strut

support intercostals inside the wings

between stations 81 and 96, in accordance

with British Aerospace Viscount Preliminary

Technical Leaflet (PTL) 332, Issue 1, Disc 11

Doc.4, dated December 2, 1991 (for Model

Viscount 744 and 745D series airplanes); or

British Aerospace Viscount PTL 203, Issue 1,

Disc 11 Doc.2, dated December 2, 1991 (for

Model Viscount 810 series airplanes); as

applicable.

(1) If no cracking is detected in the chassis

side bracing structure, repeat the inspection

thereafter at intervals not to exceed 1,500

flight hours or 14 months, whichever occurs

first.

(2) If any cracking is detected in the chassis

side bracing structure, prior to further flight,

replace the cracked side of the bracing

structure with a new structure, in accordance

with the applicable PTL.

(3) If no cracking is detected in the chassis

top strut support intercostal, prior to further

flight, perform an eddy current inspection to

determine the specification of the material

(either L72 or L73) of the intercostals, in

accordance with the applicable PTL.

(i) If the material is manufactured from

L72, prior to further flight, replace the

chassis top strut support intercostal with a

new chassis top strut support intercostal, in

accordance with the applicable PTL.

(ii) If the material is manufactured from

L73, no further action is required by

paragraph (a)(3) of this AD.

(4) If cracking is detected in the chassis top

strut support intercostal, prior to further

flight, replace it with a new chassis top strut

support intercostal, in accordance with the

applicable PTL.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) 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.

(d) The inspections and replacements shall

be done in accordance with British

Aerospace Viscount Preliminary Technical

Leaflet (PTL) 332, Issue 1, Disc 11 Doc.4,

dated December 2, 1991 (for Model Viscount

744 and 745D series airplanes); or British

Aerospace Viscount PTL 203, Issue 1, Disc 11

Doc.2, dated December 2, 1991 (for Model

Viscount 810 series airplanes); as applicable.

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 British Aerospace Regional Aircraft

Ltd., Engineering Support Manager, Military

Business Unit, Chadderton Works, Greengate,

Middleton, Manchester M24 1SA, England.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

February 3, 1995.

Issued in Renton, Washington, on

December 21, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–49 Filed 1–3–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–137–AD; Amendment

39–9107; AD 94–26–12]

Airworthiness Directives; Raytheon

Corporate Jets Model Hawker 800 and

1000 and Model DH/BH/HS/BAe 125

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon

Corporate Jets Model Hawker 800 and

1000 and Model DH/BH/HS/BAe 125

series airplanes, that requires

inspections to detect cracking of the

sidestay jack pivots of the main landing

gear, and replacement of the sidestay

jack pivot assemblies with new

assemblies. This amendment is

prompted by a report of fracturing of a

jack pivot, which resulted in the

inability of the main landing gear to

deploy. The actions specified by this AD

are intended to prevent a wheels-up

landing.

DATES: Effective February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 3,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Corporate Jets, Inc., 3

Bishops Square Street, Albans Road

West, Hatfield, Hertfordshire, AL109NE,

United Kingdom. This information may

be examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal
Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations 331

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Raytheon

Corporate Jets Model Hawker 800 and

1000 and Model DH/BH/HS/BAe 125

series airplanes was published in the

Federal Register on September 27, 1994

(49 FR 49217). That action proposed to

require inspections to detect cracking of

the sidestay jack pivots of the main

landing gear, and replacement of the

sidestay jack pivot assemblies with new

assemblies.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been added to this final rule to clarify

this requirement.

In addition, the FAA has recently

reviewed the figures it has used over the

past several years in calculating the

economic impact of AD activity. In

order to account for various inflationary

costs in the airline industry, the FAA

has determined that it is necessary to

increase the labor rate used in these

calculations from $55 per work hour to

$60 per work hour. The economic

impact information, below, has been

revised to reflect this increase in the

specified hourly labor rate.

After careful review of the available

data the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 550 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 6

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

The FAA has been advised that the

manufacturer plans to provide the

required parts at no cost to the

operators. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $198,000, or

$360 per airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from 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 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

94–26–12 Raytheon Corporate Jets, Inc.

(Formerly De Havilland; Hawker

Siddeley; British Aerospace, plc):

Amendment 39–9107. Docket 94–NM–

137–AD.

Applicability: Model Hawker 800 and 1000

series airplanes and Model DH/BH/HS/BAe

125–1A through -1000A series airplanes;

equipped with main landing gear (MLG)

sidestay assemblies on which Post-Mod

252091 steel jack pivots have been installed;

certificated in any category.

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 use the authority

provided in paragraph (f) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the inability of the MLG to

deploy and a consequent wheels-up landing,

accomplish the following:

(a) Perform a detailed visual inspection,

using a 10X magnifier, to detect cracking of

the sidestay assembly jack pivot of the left

and right MLG, in accordance with Raytheon

Corporate Jets Service Bulletin SB 32–233,

dated June 24, 1994, at the latest of the times

specified in paragraphs (a)(1), (a)(2), or (a)(3)

of this AD.

(1) Within 28 days after the effective date

of this AD; or

(2) Prior to the accumulation of 3,000 total

landings on the sidestay assembly since new;

or

(3) Prior to the accumulation of 1,000 total

landings since overhaul of the sidestay

assembly.

(b) If no cracks are found and the sidestay

assembly has been overhauled prior to the

accomplishment of the inspection specified

in paragraph (a) of this AD: Accomplish the

requirements of paragraphs (b)(1) and (b)(2)

of this AD in accordance with Raytheon

Corporate Jets Service Bulletin SB 32–233,

dated June 24, 1994.

(1) Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 1,000 landings.

(2) Prior to the accumulation of 4,000 total

landings on the jack pivot assembly since the

sidestay assembly was last overhauled, or

within 300 landings after the effective date of

this AD, whichever occurs later: Replace the

jack pivot assembly with a new assembly.
332 Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Rules and Regulations

Thereafter, prior to the accumulation of 4,000

landings, remove the jack pivot assembly and

replace it with a new assembly in accordance

with the service bulletin.

(c) If no cracks are found and the sidestay

assembly has not been overhauled prior to

accomplishment of the inspection required

by paragraph (a) of this AD: Prior to the

accumulation of 4,000 total landings on the

jack pivot assembly, or within 300 landings

after the effective date of this AD, whichever

occurs later, replace the jack pivot assembly

with a new assembly in accordance with

Raytheon Corporate Jets Service Bulletin SB

32–233, dated June 24, 1994. Thereafter,

prior to the accumulation of 4,000 landings

on the jack pivot assembly, replace it with a

new assembly in accordance with the service

bulletin.

(d) If any crack is found that does not

exceed the limits specified in Raytheon

Corporate Jets Service Bulletin SB 32–233,

dated June 24, 1994, accomplish the

requirements of paragraphs (d)(1), (d)(2), or

(d)(3) of this AD, as applicable, in accordance

with the service bulletin.

(1) For sidestay assemblies that have

accumulated 4,000 or more total landings

since new that have been overhauled prior to

accomplishment of the inspection specified

in paragraph (a) of this AD: Accomplish

paragraphs (d)(1)(i) and (d)(1)(ii) of this AD.

(i) Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 100 landings.

(ii) Prior to the accumulation of 4,000 total

landings on the jack pivot assembly since the

sidestay assembly was last overhauled, or

within 300 landings after the effective date of

this AD, whichever occurs later: Replace the

jack pivot assembly with a new assembly.

Thereafter, prior to the accumulation of 4,000

landings on the jack pivot assembly, replace

it with a new assembly in accordance with

the service bulletin.

(2) For any sidestay assemblies that have

accumulated 4,000 or more total landings

since new that have not been overhauled:

Accomplish paragraphs (d)(2)(i) and (d)(2)(ii)

of this AD.

(i) Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 100 landings.

(ii) Within 300 landings after the effective

date of this AD, replace the jack pivot

assembly with a new assembly. Thereafter,

prior to the accumulation of 4,000 landings

on the jack pivot assembly, replace it with a

new assembly in accordance with the service

bulletin.

(3) For sidestay assemblies that have

accumulated less than 4,000 total landings

since new: Accomplish paragraphs (d)(3)(i)

and (d)(3)(ii) of this AD.

(i) Repeat the inspection required by

paragraph (a) of this AD thereafter at

intervals not to exceed 100 landings.

(ii) Prior to the accumulation of 4,000 total

landings on the jack pivot assembly, or

within 300 landings after the effective date of

this AD, whichever occurs later, replace the

jack pivot assembly with a new assembly.

Thereafter, prior to the accumulation of 4,000

landings on the jack pivot assembly, replace

it with a new assembly in accordance with

the service bulletin.

(e) If, during any inspection required by

this AD, any crack is found that exceeds the

limits specified in paragraph 2.B.(6)(c) of the

Accomplishment Instructions of Raytheon

Corporate Jets Service Bulletin SB 32–233,

dated June 24, 1994: Prior to further flight,

replace the cracked pivot assembly with a

new assembly in accordance with the service

bulletin. Thereafter, prior to the

accumulation of 4,000 landings on the jack

pivot assembly, replace it with a new

assembly in accordance with the service

bulletin.

(f) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) 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.

(h) The inspections and replacements shall

be done in accordance with Raytheon

Corporate Jets Service Bulletin SB 32–233,

dated June 24, 1994. 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 Raytheon Corporate Jets, Inc.,

3 Bishops Square Street, Albans Road West,

Hatfield, Hertfordshire, AL109NE, United

Kingdom. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(i) This amendment becomes effective on

February 3, 1995.

Issued in Renton, Washington, on

December 21, 1994.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–50 Filed 1–3–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–NM–229–AD; Amendment

39–9103; AD 94–26–08]

Airworthiness Directives; Fokker

Model F27 Series Airplanes (Excluding

Mark 050 Series Airplanes)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F27

series airplanes, that requires

accomplishment of certain structural

modifications. This amendment is

prompted by reports of incidents

involving fatigue cracking and corrosion

in transport category airplanes that are

approaching or have exceeded their

economic design goal. These incidents

have jeopardized the airworthiness of

the affected airplanes. The actions

specified by this AD are intended to

prevent degradation in the structural

capabilities of the affected airplanes.

This action also reflects the FAA’s

decision that long term continued

operational safety should be assured by

actual modification of the airframe

rather than repetitive inspections.

DATES: Effective February 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 3,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Mark Quam, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2145; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Fokker

Model F27 series airplanes was

published in the Federal Register on

March 14, 1994 (59 FR 11737). That

action proposed to require certain

structural modifications of certain

Fokker Model F27 series airplanes prior

to their economic design goal. –

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received. –

One commenter supports the

proposed rule. –

One commenter requests a revision to

the applicability statement to specify

the series of Fokker Model F27 airplanes