Federal Register / Vol. 61, No. 117 / Monday, June 17, 1996 / Rules and Regulations 30505

(b) For airplanes with torque putty between

the engine filter adapter assembly, nut, and

oil pump housing, inspect the torque putty

for misalignment, evidence of oil leakage, or

cracks.

(1) If any misalignment, evidence of oil

leakage, or torque putty cracks are found,

prior to further flight, accomplish the

requirements specified in paragraph (a) of

this AD, including all subparagraphs.

(2) If no misalignment, evidence of oil

leakage, or torque putty cracks are found,

reinspect at intervals not to exceed 100 hours

TIS until the engine oil filter is removed.

(c) Replacing the engine oil filter adapter

assembly does not eliminate the repetitive

inspection requirement of this AD.

(d) The repetitive inspections of the torque

putty as required by this AD may be

performed by the owner/operator holding at

least a private pilot certificate as authorized

by section 43.7 of the Federal Aviation

Regulations (14 CFR 43.7), and must be

entered into the aircraft records showing

compliance with this AD in accordance with

section 43.11 of the Federal Aviation

Regulations (14 CFR 43.11).

(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 initial or repetitive

compliance time that provides an equivalent

level of safety may be approved by the

Manager, Wichita Aircraft Certification Office

(ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209.

The request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Wichita ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(g) Information related to this AD may be

examined at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106.

(h) This amendment (39–9665) becomes

effective on July 31, 1996.

Issued in Kansas City, Missouri, on June 3,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–14631 Filed 6–14–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–05–AD; Amendment 39–

9591; AD 96–09–15]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Models 208 and

208B Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This action makes a

correction to Airworthiness Directive

(AD) 96–09–15 concerning all Cessna

Aircraft Company (Cessna) Models 208

and 208B airplanes, which was

published in the Federal Register on

May 7, 1996 (61 FR 20641). That

publication incorrectly references a cue

for the pilot or crew member in severe

icing conditions. The AD currently

requires the pilot to follow certain

visual cues during flight in icing

conditions and the third of these cues

requires the pilot to look at the engine

propeller spinner. This cue is

inappropriate for this type of airplane.

The intent of the AD in paragraph (a)

(1), first bullet, third cue, should not be

a requirement for the Cessna Models

208 and 208B. This action corrects the

AD to reflect this change.

EFFECTIVE DATE: June 11, 1996.

FOR FURTHER INFORMATION CONTACT: Mr.

John Dow, Aerospace Engineer, FAA,

Small Airplane Directorate, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: On May 7,

1996, the Federal Aviation

Administration (FAA) issued AD 96–

09–15, Amendment 39–9591 (61 FR

20641, May 7, 1996), which applies to

all Cessna Models 208 and 208B

airplanes. This AD requires a revision in

the Airplane Flight Manual (AFM) by

incorporating a warning into the

Limitations Section of the AFM. Within

this warning (in the first bulleted

paragraph) are cues for the pilot to

follow during flight in severe icing

conditions. The third cue references

accumulation of ice on the engine

propeller spinner.

Need for the Correction

The AD incorrectly references the

‘‘* * * engines propeller spinner

* * *’’ which is not appropriate for the

type design of these Cessna Models 208

and 208B airplanes. These airplanes are

single engine designs which would not

allow the pilot to see the engine

propeller spinner from the cockpit.

Correction of Publication

Accordingly, the publication of May

7, 1996 (61 FR 20641), of Amendment

39–9591; AD 96–09–15, which was the

subject of FR Doc. 96–10729, is

corrected as follows:

§ 39.13 [Corrected]

On page 20642, in the third column,

section 39.13, paragraph (a) (1), line 17

from the top of the column, disregard

and delete ‘‘-Accumulation of ice on the

engine propeller spinner * * *’’.

Action is taken herein to clarify this

requirement of AD 96–09–15 and to add

this AD correction to section 39.13 of

the Federal Aviation Regulations (14

CFR 39.13).

The effective date remains June 11, 1996.

Issued in Kansas City, Missouri on June 10,

1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–15139 Filed 6–14–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 93–CE–34–AD; Amendment 39–

9670; AD 96–13–02]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Aircraft Limited (Formerly British

Aerospace, Regional Airlines Limited)

Jetstream Model 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Jetstream Aircraft

Limited (JAL) Jetstream Model 3201

airplanes. This action requires

repetitively inspecting the spigot

housing plate for cracks and corrosion at

the wing/fuselage forward attachment

sliding joint, replacing any cracked or

corroded part, and eventually replacing

the spigots and spigot housing plate

with new parts of improved design. A

crack in the spigot housing plate

assembly found during fatigue testing of

the affected airplanes prompted this

action. The actions specified by this AD

are intended to prevent structural

failure of the wing/fuselage area caused

by a cracked or corroded spigot housing

assembly.

DATES: Effective August 7, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

1996.